Supersonic air inlet analysis comprehensive modeling system based on aero-engine

Abstract

The invention discloses a supersonic air inlet channel analysis comprehensive modeling system based on an aero-engine, which comprises a data acquisition module, an air inlet pressure analysis module, an air inlet channel temperature analysis module, a model construction evaluation module and a historical data storage module, and relates to the technical field of aero-engine air inlet channel analysis. According to the supersonic air inlet channel analysis comprehensive modeling system based on the aero-engine, the service life and the maintenance time of the air inlet channel in the whole working condition environment can be analyzed more comprehensively by considering the change of the pressure borne by the air inlet channel of the engine and the temperature of all positions of the air inlet channel on the fatigue degree; according to the method, the purpose of comprehensively and accurately completing comprehensive and reliable evaluation of the engine air inlet channel is well achieved, the reliability of an evaluation analysis result is greatly improved, and the air inlet channel is more comprehensively evaluated in combination with the temperature on the basis of pressure data of the blade tip of the press machine; the comprehensive fatigue strength analysis of the temperature change conditions of the front section, the middle part and the tail end of the air inlet channel is realized.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine inlet analysis, and specifically to a supersonic inlet analysis integrated modeling system based on an aero-engine. Background Art

[0002] The stability of the compressor is a prerequisite for the stable operation of an aero-engine. Estimating the stability of the compressor and ensuring that the compressor operates away from the surge boundary are the basis for ensuring the stable operation of the engine. Currently, by establishing a tip static pressure model of the compressor, the tip static pressure signal of the compressor can be accurately restored, reducing the cost of compressor experiments, realizing digital simulation of the tip pressure signal of the compressor, and based on this, digital simulation design experiments for compressor stability control can be carried out.

[0003] Referring to a method for modeling the tip static pressure of an axial-flow compressor with the Chinese patent publication number CN105404717B, the established tip static pressure model of the compressor has good signal restoration, and can effectively simulate the dynamic static pressure signal of the tip static pressure of the compressor under stable conditions and near-surge conditions; at the same time, the established tip static pressure model of the compressor has a high degree of coincidence with the actual situation, and the autocorrelation error between it and the actual compressor experimental data can be guaranteed not to exceed 5%.

[0004] Referring to a method for modeling a mode conversion model of a combined power propulsion system with the Chinese patent publication number CN115221807A, by using the NPV model to reflect the time-varying and non-linear characteristics of the engine, the modeling difficulty problem caused by the large span of the altitude Mach number of the combined power engine can be effectively solved. In addition, the NPV models of each sub-engine are connected in parallel, and the coupling of the inlet splitter plate angle is considered, and a common working model of each sub-engine system during the mode conversion period is established, so as to effectively achieve a smooth transition of thrust during the mode conversion and achieve a large range of thrust.

[0005] Based on a comprehensive analysis of the above reference patents, the following defects can be obtained:

[0006] The analysis factors of the existing engine inlet evaluation and analysis system are relatively single, resulting in a low reliability of the evaluation and analysis results. Evaluating the inlet only by analyzing the pressure and tip pressure data of the compressor is not comprehensive enough, and it is impossible to consider the changes in the pressure received by the engine inlet and the temperature at each position of the airway on the fatigue strength, so as to more comprehensively analyze the service life and maintenance time of the inlet under the entire working condition environment of the inlet, and it is impossible to achieve the purpose of comprehensively and accurately evaluating the engine inlet comprehensively and reliably. It is impossible to conduct a comprehensive fatigue strength analysis on the temperature change conditions of the front section, middle section and end section of the inlet, which brings great inconvenience to the working condition evaluation and analysis of the engine inlet. Summary of the Invention

[0007] (1) Technical problems to be solved

[0008] In view of the deficiencies of the prior art, the present invention provides a supersonic inlet analysis and comprehensive modeling system based on an aeroengine, which solves the problems that the analysis factors of the existing engine inlet evaluation and analysis system are relatively single, resulting in low reliability of the evaluation and analysis results. Evaluating the inlet only by analyzing the pressure and tip pressure data of the compressor is not comprehensive enough, and it is impossible to consider the pressure on the engine inlet and the change of temperature at each position of the air passage on the fatigue strength, so as to more comprehensively analyze the service life and maintenance time of the inlet under the entire working condition environment of the inlet, and it is impossible to achieve the purpose of comprehensively and accurately evaluating the engine inlet reliably, and it is impossible to comprehensively analyze the temperature change of the front, middle and end sections of the inlet for fatigue strength analysis.

[0009] (2) Technical solutions

[0010] To achieve the above objectives, the present invention is realized through the following technical solutions: A supersonic inlet analysis and comprehensive modeling system based on an aeroengine, including a data acquisition module, an intake pressure analysis module, an inlet temperature analysis module, a model construction and evaluation module, and a historical data storage module;

[0011] The data acquisition module is used to collect the wind resistance pressure f at the front section of the engine inlet, the temperature T at the front end of the inlet n1 , the temperature T at the middle section of the inlet n2 and the temperature T at the end of the inlet n3 ;

[0012] The intake pressure analysis module is used to analyze and process the intake pressure F of the inlet by combining the wind resistance pressure f at the front section of the engine inlet collected by the data acquisition module with the compressor tip pressure model, and create an intake pressure analysis model;

[0013] The inlet temperature analysis module is used to establish a temperature and inlet fatigue strength analysis model according to the temperature T at the front end of the inlet n1 , the temperature T at the middle section of the inlet n2 and the temperature T at the end of the inlet n3 collected by the data acquisition module respectively, so as to analyze the specific operation data of the engine inlet at different temperatures;

[0014] The model construction and evaluation module is used to combine the intake pressure analysis model and the temperature analysis model to create an inlet comprehensive analysis model, so as to evaluate the operation stability of the engine inlet under different intake pressures and temperature conditions;

[0015] The historical data storage module is used to store the data of each simulation evaluation by the model construction and evaluation module, so that the model construction and evaluation module can extract and combine the current data for comprehensive evaluation.

[0016] Preferably, the intake pressure analysis module creates an intake pressure analysis model, which specifically includes the following steps:

[0017] S1. By combining the compressor tip pressure model and the wind resistance pressure f at the front section of the engine intake duct, calculate the intake pressure correction coefficient X of the intake duct. The calculation formula is as follows:

[0018] X = αC p + βf;

[0019] where C p is the compressor tip static pressure coefficient, α is the compressor tip pressure evaluation weight, and β is the wind resistance pressure evaluation weight at the front section of the air duct;

[0020] S2. According to the intake pressure correction coefficient X calculated in step S2, correct the intake pressure F of the engine intake duct, and calculate the corrected intake pressure F 修正 of the intake duct. The specific formula is as follows:

[0021] F 修正 = Xe -2 + F.

[0022] Preferably, the compressor tip pressure model calculates the compressor tip static pressure coefficient C p by combining the blade passage static pressure model, the tip stall pulsation model, and the tip stall damping correction model. The specific calculation formula is:

[0023]

[0024] where is the compressor blade passage static pressure coefficient, K m is the compressor tip stall damping correction coefficient, is the compressor tip stall pulsation static pressure coefficient.

[0025] Preferably, in step S1, α + β = 1.

[0026] Preferably, the intake duct temperature analysis module establishes a temperature analysis model, which specifically includes the following steps:

[0027] E1. Since during the actual use of the intake duct, the front end of the intake duct is significantly affected by air friction, so the temperature will rise rapidly. The middle part of the intake duct is less affected by air friction and the temperature change is not obvious. The end of the intake duct is connected to the engine combustion chamber and the temperature change is the largest. Therefore, the collected front-end temperature T n1 of the intake duct, the middle temperature T n2 of the intake duct, and the end temperature T n3 of the intake duct are subjected to comprehensive mean value evaluation processing. The specific formula is as follows:

[0028]

[0029] Among them, a is the average temperature at the front end of the intake duct, b is the average temperature in the middle of the intake duct, c is the average temperature at the end of the intake duct, and T i1 is the temperature value at the front end of the intake duct during the i-th temperature evaluation, and T i2 is the temperature value in the middle of the intake duct during the i-th temperature evaluation, and T i3 is the temperature value at the end of the intake duct during the i-th temperature evaluation;

[0030] E2. Comprehensively evaluate the fatigue strength Y of the intake duct based on the average temperature of each part of the intake duct calculated in step E1 and the fatigue strength of the intake duct material itself. The specific formula is as follows:

[0031] Y = (1 - e -(a+n+c) ) × Y 出厂 ;

[0032] Among them, Y 出厂 is the fatigue strength of the intake duct material itself when it leaves the factory;

[0033] E3. Analyze and predict the service life of the intake duct under the influence of temperature based on the change of the fatigue strength Y of the intake duct calculated in step E2 during each evaluation process.

[0034] Preferably, the steps for the model construction and evaluation module to create an integrated analysis model of the intake duct are as follows:

[0035] U1. Count the number Z of times when the intake pressure in the intake pressure analysis model is greater than the standard corrected pressure F 修正 for the intake duct during the corrected intake pressure F 标准 ;

[0036] U2. Count the maximum fatigue strength Y max , the minimum fatigue strength Y min of the intake duct, and the average fatigue strength Y R of the intake duct during k evaluations in the temperature analysis model;

[0037] U3. Calculate the comprehensive evaluation system W of the intake duct according to the various data counted in steps U1 and U2. The specific formula is as follows:

[0038]

[0039] U4. When W is less than the standard evaluation coefficient W 标 , it means that the entire engine intake duct is in a safe operating condition;

[0040] When W is greater than or equal to the standard evaluation coefficient W 标When this occurs, it indicates that the entire engine intake duct is in a dangerous working condition that requires inspection, maintenance, and servicing on schedule.

[0041] Preferably, the fatigue strength Y of the average intake duct in step U2 R has the following specific calculation formula:

[0042]

[0043] where Y i is the fatigue strength value of the i-th intake duct temperature evaluation and analysis.

[0044] Preferably, the historical data storage module is one of a MySQL database or a SQL Server database.

[0045] (III) Beneficial Effects

[0046] The present invention provides a supersonic intake duct analysis and comprehensive modeling system based on an aeroengine. Compared with the prior art, it has the following beneficial effects: The supersonic intake duct analysis and comprehensive modeling system based on an aeroengine includes a data acquisition module, an intake pressure analysis module, an intake duct temperature analysis module, a model construction and evaluation module, and a historical data storage module. The data acquisition module is used to collect the wind resistance pressure f at the front section of the engine intake duct, the temperature T n1 at the front end of the intake duct, the temperature T n2 in the middle of the intake duct, and the temperature T n3 at the end of the intake duct. The intake pressure analysis module is used to analyze and process the wind resistance pressure f at the front section of the engine intake duct collected by the data acquisition module in combination with the compressor tip pressure model to create an intake pressure analysis model. It can realize the analysis of the service life and maintenance time of the intake duct under the entire working condition environment by considering the pressure on the engine intake duct and the change of fatigue strength with the temperature at each position of the air duct, and well achieves the purpose of comprehensively and accurately evaluating the engine intake duct reliably, greatly improving the reliability of the evaluation and analysis results. Based on the compressor tip pressure data, a more comprehensive evaluation of the intake duct is carried out in combination with the temperature, and a comprehensive fatigue strength analysis of the temperature change conditions at the front, middle, and end of the intake duct is realized, thus greatly facilitating the evaluation and analysis of the working condition of the engine intake duct. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] Figure 1 is a structural principle block diagram of the system of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0048] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0049] Please refer to Figure 1 , the embodiments of the present invention provide two technical solutions: a supersonic inlet analysis and comprehensive modeling system based on an aeroengine, which specifically includes the following embodiments:

[0050] Embodiment 1: A supersonic inlet analysis and comprehensive modeling system based on an aeroengine, including a data acquisition module, an intake pressure analysis module, an intake duct temperature analysis module, a model construction and evaluation module, and a historical data storage module;

[0051] The data acquisition module is used to collect the wind resistance pressure f at the front section of the engine intake duct, the temperature T at the front end of the intake duct n1 , the temperature T at the middle section of the intake duct n2 and the temperature T at the end of the intake duct n3 ;

[0052] The intake pressure analysis module is used to analyze and process the intake pressure F of the intake duct by combining the wind resistance pressure f collected by the data acquisition module at the front section of the engine intake duct with the compressor tip pressure model, and create an intake pressure analysis model;

[0053] The intake duct temperature analysis module is used to establish a temperature and intake duct fatigue strength analysis model according to the temperature T at the front end of the intake duct n1 , the temperature T at the middle section of the intake duct n2 and the temperature T at the end of the intake duct n3 collected by the data acquisition module respectively, so as to analyze the specific operation data of the engine intake duct at different temperatures;

[0054] The model construction and evaluation module is used to combine the intake pressure analysis model and the temperature analysis model to create an intake duct comprehensive analysis model, so as to evaluate the operation stability of the engine intake duct under different intake pressures and temperature conditions;

[0055] The historical data storage module is used to store the data of each simulation and evaluation by the model construction and evaluation module, so that the model construction and evaluation module can extract and combine the current data for comprehensive evaluation.

[0056] In the embodiments of the present invention, the specific steps for the intake pressure analysis module to create an intake pressure analysis model include the following:

[0057] S1. Calculate the intake pressure correction coefficient X of the intake duct by combining the compressor tip pressure model and the wind resistance pressure f at the front section of the engine intake duct. The calculation formula is as follows:

[0058] X = αC p + βf;

[0059] Where C p is the static pressure coefficient at the compressor tip, α is the evaluation weight of the compressor tip pressure, and β is the evaluation weight of the wind resistance pressure at the front section of the air duct;

[0060] S2. Correct the intake pressure F of the engine intake duct according to the intake pressure correction coefficient X calculated in step S2, and calculate the corrected intake pressure F 修正 of the intake duct. The specific formula is as follows:

[0061] F 修正 = Xe -2 + F.

[0062] In the embodiment of the present invention, the compressor tip pressure model calculates the static pressure coefficient C p at the compressor tip by combining the blade passage static pressure model, the tip stall pulsation model and the tip stall damping correction model. The specific calculation formula is:

[0063]

[0064] Where is the static pressure coefficient of the compressor blade passage, K m is the compressor tip stall damping correction coefficient, is the static pressure coefficient of the compressor tip stall pulsation.

[0065] In the embodiment of the present invention, the method for constructing the compressor tip pressure model specifically includes the following steps:

[0066] S1. Establish a compressor blade phase model, and calculate the pulsation phase of the compressor blade passage static pressure pulsation at the current sampling moment and the tip stall pulsation phase of the compressor tip at the current sampling moment. The calculation formula of the pulsation phase at the current sampling moment is:

[0067]

[0068] Where is the pulsation phase at the previous sampling moment, ΔT is the sampling period, and ω is the pulsation period;

[0069] The compressor blade passage static pressure pulsation phase Obtained by the following formula:

[0070]

[0071] Wherein, is the static pressure pulsation phase of the compressor blade passage at the previous sampling moment, ΔT is the sampling period, N is the rotational speed of the compressor rotor, and N um is the number of compressor rotor blades;

[0072] The static pressure pulsation phase of the compressor tip stall at the current sampling moment Obtained by the following formula:

[0073]

[0074] Wherein, is the static pressure pulsation phase of the compressor tip stall at the previous sampling moment, ΔT is the sampling period, N is the rotational speed of the compressor rotor, n is a preset constant, and the value of n is 3.

[0075] S2. Establish a static pressure model of the compressor blade passage using a third-order Fourier series model, and calculate the static pressure coefficient of the compressor blade passage The specific calculation formula is:

[0076]

[0077] Wherein, is the static pressure pulsation phase of the compressor blade passage at the current sampling moment;

[0078] S3. Establish a tip stall pulsation model of the compressor using a third-order Fourier series model, and calculate the static pressure coefficient of the tip stall pulsation of the compressor The specific calculation formula is;

[0079]

[0080] Wherein, is the static pressure pulsation phase of the compressor tip stall at the current sampling moment,

[0081] K1 = -0.3297·x 3 +0.0843·x 2 -0.0083·x + 6.1226·10 -4 ;

[0082] K2 = -0.3087·x 3 +0.0876·x 2 -0.0082·x + 3.4755·10 -4 ;

[0083] K3 = 0.2603·x 3-0.0731·x 2 +0.0069·x - 3.2524·10 -4 ;

[0084] P1 = 0.0237·x 3 +0.0171·x 2 -5.996·10 -4 ·x - 6.1274·10 -4 ;

[0085] P2 = -0.2942·x 3 +0.0785·x 2 -0.0076·x + 4.7065·10 -4 ;

[0086] P3 = 0.0066·x 3 -7.7619·10 -4 ·x 2 +1.0115·10 -4 ·x - 3.194·10 -4 ;

[0087] x is the surge margin of the compressor;

[0088] S4. Establish a compressor tip stall damping correction model and calculate the compressor tip stall damping correction coefficient K m , and the specific calculation formula is:

[0089]

[0090] where, is the damping zero point, and the damping zero point is the compressor tip stall pulsation phase at the current sampling moment;

[0091] S5. Calculate the compressor tip static pressure model from the phase model, blade passage static pressure model, tip stall pulsation model and tip stall damping correction model, that is, calculate the compressor tip static pressure coefficient C p , and the specific calculation formula is:

[0092]

[0093] where, is the blade passage static pressure coefficient of the compressor, and K m is the compressor tip stall damping correction coefficient, is the compressor tip stall pulsation static pressure coefficient.

[0094] In the embodiment of the present invention, α + β = 1 in step S1.

[0095] Example 2: The different technical solution of this embodiment of the present invention compared with Embodiment 1 lies in that: the specific steps for the intake port temperature analysis module to establish a temperature analysis model are as follows:

[0096] E1. Since during the actual use of the intake port, the front end of the intake port is significantly affected by air friction, the temperature will rise rapidly. The middle part of the intake port is less affected by air friction and the temperature change is not obvious. The end of the intake port is connected to the engine combustion chamber and has the largest temperature change. Therefore, the collected temperature T at the front end of the intake port n1 , the temperature T in the middle of the intake port n2 and the temperature T at the end of the intake port n3 are subjected to comprehensive mean value evaluation processing. The specific formula is as follows:

[0097]

[0098] Among them, a is the mean temperature at the front end of the intake port, b is the mean temperature in the middle of the intake port, c is the mean temperature at the end of the intake port, T i1 is the temperature value at the front end of the intake port during the i-th temperature evaluation, T i2 is the temperature value in the middle of the intake port during the i-th temperature evaluation, T i3 is the temperature value at the end of the intake port during the i-th temperature evaluation;

[0099] E2. According to the mean temperature of each part of the intake port calculated in step E1 and the fatigue strength of the intake port material itself, comprehensively evaluate the fatigue strength Y of the intake port. The specific formula is as follows:

[0100] Y = (1 - e -(a+b+c) ) × Y 出厂 ;

[0101] Among them, Y 出厂 is the fatigue strength of the intake port material itself when it leaves the factory;

[0102] E3. Analyze and predict the service life of the intake port under the influence of temperature based on the change of the fatigue strength Y of the intake port calculated in step E2 during each evaluation process.

[0103] In this embodiment of the present invention, the specific steps for the model construction and evaluation module to create an intake port comprehensive analysis model are as follows:

[0104] U1. Count the number Z of times that the intake port in the intake pressure analysis model has a corrected intake pressure F 修正 greater than the standard corrected pressure F 标准 ;

[0105] U2. Count the maximum fatigue strength Y max of the intake port and the minimum fatigue strength Y min of the intake port during k evaluations in the temperature analysis model.and the fatigue strength Y of the average intake passage R ;

[0106] U3. Calculate the comprehensive evaluation system W of the intake passage according to the various data statistically obtained in steps U1 and U2. The specific formula is as follows:

[0107]

[0108] U4. When W is less than the standard evaluation coefficient W 标 , it indicates that the entire engine intake passage is in a safe operating condition;

[0109] When W is greater than or equal to the standard evaluation coefficient W 标 , it indicates that the entire engine intake passage is in a dangerous operating condition to be overhauled and requires regular inspection, maintenance, and servicing.

[0110] In the embodiment of the present invention, in step U2, the specific calculation formula of the fatigue strength Y of the average intake passage R is as follows:

[0111]

[0112] where Y i is the fatigue strength value of the i-th intake passage temperature evaluation and analysis.

[0113] In the embodiment of the present invention, the historical data storage module adopts one of the MySQL database or the SQL Server database.

[0114] In summary, the present invention can realize considering the pressure on the engine intake passage and the change of fatigue strength caused by the temperature at each position of the air passage, so as to more comprehensively analyze the service life and maintenance time of the intake passage under the entire operating condition environment, and well achieve the purpose of comprehensively and accurately completing the comprehensive and reliable evaluation of the engine intake passage, greatly improving the reliability of the evaluation and analysis results. Based on the tip pressure data of the compressor, a more comprehensive evaluation of the intake passage is carried out in combination with the temperature, and a comprehensive fatigue strength analysis of the temperature change conditions at the front, middle, and end of the intake passage is realized, thus greatly facilitating the evaluation and analysis of the operating condition of the engine intake passage.

[0115] At the same time, the content not described in detail in this specification belongs to the prior art well-known to those skilled in the art.

[0116] It should be noted that, in this text, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variation thereof is intended to cover non-exclusive inclusion, such that a process, method, article or device comprising a series of elements not only includes those elements but also includes other elements not expressly listed, or elements inherent to such process, method, article or device.

[0117] Although the embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A comprehensive modeling system for supersonic inlet analysis based on an aircraft engine, characterized by: It includes data acquisition module, intake pressure analysis module, intake duct temperature analysis module, model building and evaluation module and historical data storage module; The data acquisition module is used to collect the engine intake duct front section wind resistance pressure f, intake duct front end temperature T n1 , the temperature in the middle of the inlet duct T n2 and the inlet end temperature T n3 ; The intake pressure analysis module is used to analyze and process the intake pressure F of the intake duct by combining the engine intake duct front section windage pressure f collected by the data collection module with the compressor blade tip pressure model, and create an intake pressure analysis model; The intake duct temperature analysis module is used to analyze the intake duct front end temperature T collected by the data collection module. n1 , the temperature in the middle of the inlet duct T n2 and the inlet end temperature T n3 Establish temperature and intake duct fatigue strength analysis models to analyze specific operating data of the engine intake duct at different temperatures; The model building evaluation module is used to combine the intake pressure analysis model and the temperature analysis model to create an intake duct comprehensive analysis model to evaluate the operating stability of the engine intake duct under different intake pressure and temperature conditions; The historical data storage module is used to store the data of each simulation evaluation of the model building and evaluation module, so that the model building and evaluation module can extract and combine the current data for comprehensive evaluation.

2. The comprehensive modeling system for supersonic inlet analysis based on an aircraft engine according to claim 1, characterized in that: The intake pressure analysis module creates an intake pressure analysis model, specifically comprising the following steps: S1. The intake pressure correction coefficient X of the intake duct is calculated by combining the compressor blade tip pressure model and the engine intake duct front section windage pressure f. The calculation formula is as follows: X=αC p +βf; Among them, C p is the compressor tip static pressure coefficient, α is the compressor tip pressure assessment weight, and β is the airway front section wind resistance pressure assessment weight; S2, according to the intake pressure correction coefficient X calculated in step S2 and the intake pressure F of the engine intake duct, calculate the corrected intake pressure F of the intake duct 修正 , the specific formula is as follows: F 修正 =Car -2 +F.

3. The comprehensive modeling system for supersonic inlet analysis based on an aircraft engine according to claim 2, characterized in that: The compressor tip pressure model is to calculate the compressor tip static pressure coefficient C by combining the blade passage static pressure model, the blade tip stall pulsation model and the blade tip stall damping correction model. p , the specific calculation formula is: in, is the static pressure coefficient of the compressor blade passage, K m is the compressor tip stall damping correction factor, is the static pressure coefficient of compressor blade tip stall pulsation.

4. The comprehensive modeling system for supersonic inlet analysis based on an aircraft engine according to claim 2, characterized in that: In the step S1, α+β=1.

5. The comprehensive modeling system for supersonic inlet analysis based on an aircraft engine according to claim 2, characterized in that: The inlet duct temperature analysis module establishes a temperature analysis model specifically including the following steps: E1. During the actual use of the intake duct, the front end of the intake duct is subject to more obvious air friction, so the temperature will rise rapidly, while the middle part of the intake duct receives less air friction and the temperature change is not obvious. The end of the intake duct is connected to the engine combustion chamber and the temperature change is the largest. Therefore, the collected temperature T of the front end of the intake duct is n1 , the temperature in the middle of the inlet duct T n2 and the inlet end temperature T n3 Perform comprehensive mean evaluation processing, the specific formula is as follows: Where a is the mean temperature at the front end of the inlet duct, b is the mean temperature at the middle of the inlet duct, c is the mean temperature at the end of the inlet duct, T i1 is the temperature value of the front end of the inlet duct during the i-th temperature evaluation, T i2 is the temperature value of the middle part of the inlet duct during the i-th temperature evaluation, T i3 is the temperature value of the inlet end during the i-th temperature evaluation; E2. Comprehensively evaluate the fatigue strength Y of the intake duct based on the average temperature of each part of the intake duct calculated in step E1 and the fatigue strength of the intake duct material itself. The specific formula is as follows: And=(1-e -(a+b+c) )×Y 出厂 ; Where Y 出厂 The fatigue strength of the material of the air intake duct when it leaves the factory; E3. Analyze and predict the service life of the intake duct under the influence of temperature based on the change of the fatigue strength Y of the intake duct calculated in step E2 during each evaluation process.

6. The comprehensive modeling system for supersonic inlet analysis based on an aircraft engine according to claim 5, characterized in that: The model building and evaluation module creates an intake duct comprehensive analysis model, specifically comprising the following steps: U1. In the statistical intake pressure analysis model, the intake duct is correcting the intake pressure F 修正 Greater than standard correction pressure F 标准 The number of times Z; U2, fatigue strength Y of the largest inlet duct in k evaluations in the statistical temperature analysis model max , and the minimum intake duct fatigue strength Y min And the average intake duct fatigue strength Y R ; U3. Calculate the comprehensive evaluation system W of the intake duct according to the statistical data in step U1 and step U2. The specific formula is as follows: U4, when W is less than the standard evaluation coefficient W 标 When , it means that the entire engine intake duct is in a safe operating condition; When W is greater than or equal to the standard evaluation coefficient W 标 When it is on, it means that the entire engine intake duct is in a dangerous condition awaiting maintenance and needs to be inspected and maintained on time.

7. The comprehensive modeling system for supersonic inlet analysis based on an aircraft engine according to claim 6, characterized in that: The average intake duct fatigue strength Y in step U2 R The specific calculation formula is as follows: Among them, Y i is the fatigue strength value of the i-th intake duct temperature evaluation analysis.

8. The comprehensive modeling system for supersonic inlet analysis based on an aircraft engine according to claim 1, characterized in that: The historical data storage module adopts a MySQL database or a SQL Server database.

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