Pressure-bearing casing transient stress calculation method and system, electronic equipment and storage medium

Abstract

The invention discloses a pressure-bearing casing transient stress calculation method and system, electronic equipment and a storage medium, and the method comprises the steps: dividing a working load into a plurality of independent loads without mutual influence, and determining a fitting parameter corresponding to each independent load, so as to carry out the stress analysis under the independent loads based on the fitting parameters, and according to the stress analysis result under the independent load, fitting is carried out to obtain the function relationship between different fitting parameters and the stress of the corresponding pressure-bearing casing, so that the function relationship between all the fitting parameters and the equivalent stress of the pressure-bearing casing is obtained, and the transient stress of the pressure-bearing casing can be calculated by obtaining transient parameters in a flight mission spectrum. The flight mission spectrum does not need to be simplified in the whole calculation process, the obtained transient stress is more comprehensive, the real transient stress process can be completely reflected, the transient stress is calculated through the fitting formula, the working process and workload of transient stress calculation are greatly simplified, and meanwhile the transient stress calculation time is greatly shortened.

Description

Technical Field

[0001] The present invention relates to the technical field of transient stress calculation and analysis, and in particular to a method and system for calculating transient stress of a pressure casing, electronic equipment, and a computer-readable storage medium. Background Art

[0002] As modern aircraft engine design technology places higher and higher demands on safety and economy, aircraft engine life consumption detection technology plays a very important role. Its main purpose is to determine the life consumption and remaining life of parts in real time, involving the management of engine parts life consumption data to ensure the safe use of in-service engines. As the main load-bearing component of aircraft engines, the transient stress carried by the pressure casing is crucial for life consumption. In order to quickly and accurately calculate the life consumption and remaining life of the pressure casing, a fast algorithm for stress analysis is required.

[0003] The existing transient stress calculation of the pressure casing usually adopts the finite element analysis method, such as Figure 1 As shown, it mainly includes the following steps:

[0004] 1) By simplifying the actual flight spectrum of aircraft engines, typical flight mission spectrum profiles and inertial load parameters are obtained;

[0005] 2) Complete the overall performance parameter calculation based on typical flight mission profiles;

[0006] 3) Calculate the transient mounting surface inertia load in combination with the inertia load parameters;

[0007] 4) Calculate the performance parameters of each component in combination with the overall performance parameters;

[0008] 5) Complete transient temperature field calculation and transient pressure calculation based on component performance parameters;

[0009] 6) Combine component performance parameters and transient pressure calculation results to complete transient mounting surface aerodynamic load calculation;

[0010] 7) Complete transient stress analysis by combining transient inertial load, transient temperature load, transient pressure, and transient mounting surface aerodynamic load.

[0011] Since the existing transient stress calculation method of the pressurized casing needs to simplify the flight mission spectrum to obtain the typical mission spectrum, the transient stress calculation results of some sub-cycles are omitted, and the real transient stress history cannot be fully reflected. Moreover, its transient stress calculation process is extremely complicated. It is necessary to first carry out the overall performance parameter calculation, component performance parameter calculation, transient temperature field calculation, transient aerodynamic load calculation, transient inertial load calculation, and finally carry out transient stress calculation, which is a huge workload. In addition, various load analyses need to be carried out before transient stress analysis, and some analysis processes cannot be carried out in parallel. It often takes several months from the issuance of the task to obtaining the transient stress calculation results, and the transient stress calculation is time-consuming. Summary of the invention

[0012] The present invention provides a method and system for calculating transient stress of a pressure casing, electronic equipment, and a computer-readable storage medium, which can fully reflect the actual transient stress history, greatly simplify the workflow and workload of transient stress calculation, and greatly shorten the transient stress calculation time.

[0013] According to one aspect of the present invention, a method for calculating transient stress of a pressure casing is provided, comprising the following contents:

[0014] Conduct independence analysis on the working load of the pressure casing to determine whether there is a correlation between different working loads and divide the working load into multiple independent loads;

[0015] Determine the fitting parameters corresponding to each independent load;

[0016] Based on the fitting parameters corresponding to each independent load, the stress analysis of the pressure casing under independent load is carried out, and the functional relationship between different fitting parameters and the corresponding pressure casing stress is fitted, and the functional relationship between different fitting parameters and the corresponding pressure casing stress is summed up to obtain the functional relationship between all fitting parameters and the equivalent stress of the pressure casing;

[0017] The transient parameters in the flight mission spectrum are obtained, and the transient stress of the pressure casing is calculated by combining the functional relationship between all fitting parameters and the equivalent stress of the pressure casing.

[0018] Further, the independent loads include temperature loads, gas loads, heading inertia loads, lateral inertia loads, vertical inertia loads, pitch gyro loads, and yaw gyro loads.

[0019] Furthermore, the fitting parameter corresponding to the temperature load is the engine exhaust temperature, the fitting parameter corresponding to the gas load is the engine intake pressure and the compressor outlet pressure, the fitting parameter corresponding to the heading inertia load is the engine heading inertia load coefficient, the fitting parameter corresponding to the lateral inertia load is the engine lateral inertia load coefficient, the fitting parameter corresponding to the vertical inertia load is the engine vertical inertia load coefficient, the fitting parameter corresponding to the pitch gyro load is the aircraft pitch angular velocity, and the fitting parameter corresponding to the yaw gyro load is the aircraft yaw angular velocity.

[0020] Furthermore, the functional relationship between the engine exhaust temperature and the pressure casing stress under temperature load is:

[0021]

[0022] Among them, σ T It represents the stress of the pressure casing under temperature load, and a1, a2 and a3 are all constants.

[0023] Furthermore, the functional relationship between the engine intake pressure and the compressor outlet pressure and the pressure casing stress under gas load is:

[0024]

[0025] Among them, σ P represents the pressure casing stress under gas load, b1 and b2 are constants, P3 represents the compressor outlet pressure, and P1 represents the engine inlet pressure.

[0026] Furthermore, the functional relationship between the engine heading inertia load coefficient and the pressure casing stress under the heading inertia load is:

[0027]

[0028] in, represents the stress of the pressure casing under the heading inertial load, c1 is a constant, N x Indicates the engine heading inertia load factor.

[0029] Furthermore, the functional relationship between the engine lateral inertia load coefficient and the pressure casing stress under the lateral inertia load is:

[0030]

[0031] in, It represents the stress of the pressure casing under the lateral inertia load, d1 is a constant, N y Indicates the engine lateral inertia load factor.

[0032] In addition, the present invention also provides a pressure casing transient stress calculation system, which adopts the pressure casing transient stress calculation method as described above, and comprises:

[0033] Independent load division module, used to conduct independence analysis on the working load of the pressure casing, determine whether there is a correlation between different working loads, and divide the working load into multiple independent loads;

[0034] A fitting parameter determination module, used to determine the fitting parameters corresponding to each independent load;

[0035] Functional relationship fitting module, used to carry out stress analysis on the pressure casing under independent loads based on the fitting parameters corresponding to each independent load, and to fit the functional relationship between different fitting parameters and the corresponding pressure casing stress;

[0036] The transient stress calculation module is used to obtain the transient parameters in the flight mission spectrum, and calculate the transient stress of the pressure casing by combining the functional relationship between all fitting parameters and the equivalent stress of the pressure casing.

[0037] In addition, the present invention also provides an electronic device, including a processor and a memory, wherein the memory stores a computer program, and the processor executes the steps of the above method by calling the computer program stored in the memory.

[0038] In addition, the present invention also provides a computer-readable storage medium for storing a computer program for calculating transient stress of a pressure casing, wherein the computer program executes the steps of the method described above when running on a computer.

[0039] The present invention has the following beneficial effects:

[0040] The method for calculating transient stress of a pressure casing of the present invention first performs independence analysis on the working load of the pressure casing, divides the working load into a plurality of independent loads without mutual influence, and then determines the fitting parameters corresponding to each independent load, so as to perform stress analysis under the independent load based on the fitting parameters, and obtains the functional relationship between different fitting parameters and the corresponding pressure casing stress according to the stress analysis result under the independent load, thereby obtaining the functional relationship between all fitting parameters and the equivalent stress of the pressure casing, and finally obtains the transient parameters in the flight mission spectrum to calculate the transient stress of the pressure casing. The entire calculation process does not need to simplify the flight mission spectrum, and the obtained transient stress is more comprehensive, which can fully reflect the real transient stress history, and the fitting formula is used to calculate the transient stress, which greatly simplifies the workflow and workload of transient stress calculation, and greatly shortens the transient stress calculation time.

[0041] In addition, the pressure casing transient stress calculation system of the present invention also has the above advantages.

[0042] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0044] Figure 1 It is a logical flow chart of the existing transient stress calculation method of the pressure casing.

[0045] Figure 2 It is a flow chart of a method for calculating transient stress of a pressure casing according to a preferred embodiment of the present application.

[0046] Figure 3 It is a schematic diagram of the load effect on a combustion chamber casing of a certain aircraft engine in the preferred embodiment of the present application.

[0047] Figure 4 It is a schematic diagram of stress distribution of a combustion chamber casing of a certain aircraft engine under a single temperature load in a preferred embodiment of the present application.

[0048] Figure 5 It is a schematic diagram of stress distribution of a combustion chamber casing of a certain aircraft engine under the action of a single gas load in a preferred embodiment of the present application.

[0049] Figure 6 It is a schematic diagram of stress distribution of a combustion chamber casing of a certain aircraft engine in a preferred embodiment of the present application under the action of a separate pitch gyro load.

[0050] Figure 7 It is a schematic diagram of stress distribution of a combustion chamber casing of a certain aircraft engine in a preferred embodiment of the present application under the action of a single vertical inertial load.

[0051] Figure 8 It is a schematic diagram of stress distribution of a combustion chamber casing of a certain aircraft engine in a preferred embodiment of the present application under the action of a single directional inertial load.

[0052] Fig. 9 It is a schematic diagram of the module structure of a pressure casing transient stress calculation system according to another embodiment of the present application. DETAILED DESCRIPTION

[0053] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0054] Reference Figure 2 The preferred embodiment of the present application provides a method for calculating transient stress of a pressure casing, comprising the following contents:

[0055] Step S1: Conduct independence analysis on the working load of the pressure casing to determine whether there is a correlation between different working loads and divide the working load into multiple independent loads;

[0056] Step S2: Determine the fitting parameters corresponding to each independent load;

[0057] Step S3: Based on the fitting parameters corresponding to each independent load, a stress analysis is performed on the pressure casing under an independent load, and a functional relationship between different fitting parameters and the corresponding pressure casing stress is obtained by fitting, and the functional relationship between different fitting parameters and the corresponding pressure casing stress is summed to obtain a functional relationship between all fitting parameters and the pressure casing equivalent stress;

[0058] Step S4: Obtain the transient parameters in the flight mission spectrum, and calculate the transient stress of the pressure casing by combining the functional relationship between all fitting parameters and the equivalent stress of the pressure casing.

[0059] It can be understood that the method for calculating the transient stress of the pressure casing of the present embodiment first performs an independence analysis on the working load of the pressure casing, divides the working load into multiple independent loads that do not affect each other, and then determines the fitting parameters corresponding to each independent load, so as to perform stress analysis under the independent load based on the fitting parameters, and obtains the functional relationship between different fitting parameters and the corresponding pressure casing stress according to the stress analysis results under the independent load, thereby obtaining the functional relationship between all fitting parameters and the equivalent stress of the pressure casing, and finally obtains the transient parameters in the flight mission spectrum to calculate the transient stress of the pressure casing. The entire calculation process does not require simplification of the flight mission spectrum, and the obtained transient stress is more comprehensive, which can fully reflect the actual transient stress history, and the fitting formula is used to calculate the transient stress, which greatly simplifies the workflow and workload of transient stress calculation, and greatly shortens the transient stress calculation time.

[0060] It can be understood that in step S1, the purpose of conducting independence analysis on the working load of the pressure casing is to determine whether there is mutual influence between different working loads, and to classify and divide the working load into multiple independent loads. Specifically, the working load of the pressure casing usually includes temperature load, pressure load, aerodynamic axial force, aerodynamic torque, heading inertia load, lateral inertia load, vertical inertia load, pitch gyro load and yaw gyro load, etc., among which, pressure load, aerodynamic axial force and aerodynamic torque are all generated by gas, and there is a hidden mapping relationship between them, so the pressure load, aerodynamic axial force and aerodynamic torque can be uniformly divided into gas loads, and the remaining working loads have basically no influence on each other. Therefore, the working load can be divided into multiple independent loads, and the independent loads include temperature load, gas load, heading inertia load, lateral inertia load, vertical inertia load, pitch gyro load and yaw gyro load.

[0061] It can be understood that in step S2, the relationship between each independent load and the monitorable fitting parameters is analyzed, wherein the monitorable fitting parameters include flight parameters or engine parameters, the purpose of which is to select the monitorable flight parameters or engine parameters to fit the load condition of the pressure casing, that is, to fit the stress level of the pressure casing. Specifically, the temperature load is only related to the temperature, so T6 is selected as the fitting parameter; the gas load is related to P1 and P3, so P1 and P3 are selected as the fitting parameters; the heading inertia load is related to N x So we choose N x As fitting parameters; lateral inertia load and N y So we choose N y As fitting parameters; vertical inertia load and N z So we choose N z As the fitting parameter; the pitch gyro load is related to φ, so φ is selected as the fitting parameter; the yaw gyro load is related to ψ, so ψ is selected as the fitting parameter. Among them, T6 represents the engine exhaust temperature, the unit is K; P1 represents the engine intake pressure, the unit is MPa; P3 represents the compressor outlet pressure, the unit is MPa; N x Indicates the engine heading inertia load coefficient, in g; N y Indicates the engine lateral inertia load coefficient, in g; N z It represents the vertical inertia load coefficient of the engine, in g; φ represents the pitch angular velocity of the aircraft, in rad / s; ψ represents the yaw angular velocity of the aircraft, in rad / s.

[0062] It can be understood that in step S3, based on the fitting parameters corresponding to each independent load, the finite element stress analysis of the pressure casing under independent load is carried out, and different stress conditions of each dangerous part under multiple independent load states can be obtained. The functional relationship between different fitting parameters and the corresponding pressure casing stress can be fitted through the data of several sub-samples. Among them, the functional relationship between the engine exhaust temperature and the pressure casing stress under temperature load is:

[0063]

[0064] Among them, σ T Represents the stress of the pressure casing under temperature load. a1, a2 and a3 are all constants, a1=0.00272, a2=298, a3=1.4351.

[0065] The functional relationship between the engine inlet pressure and the compressor outlet pressure and the pressure casing stress under gas load is:

[0066]

[0067] Among them, σ P It represents the pressure casing stress under gas load, b1 and b2 are constants, b1=509.53, b2=1.2426, P3 represents the compressor outlet pressure, and P1 represents the engine inlet pressure.

[0068] The functional relationship between the engine heading inertia load coefficient and the pressure casing stress under heading inertia load is:

[0069]

[0070] in, It represents the stress of the pressure casing under the heading inertial load, c1 is a constant, c1=4.3962, N x Indicates the engine heading inertia load factor.

[0071] The functional relationship between the engine lateral inertia load coefficient and the pressure casing stress under lateral inertia load is:

[0072]

[0073] in, It represents the stress of the pressure casing under the lateral inertia load, d1 is a constant, d1=13.73, N y Indicates the engine lateral inertia load factor.

[0074] The functional relationship between the engine vertical inertia load coefficient and the pressure casing stress under vertical inertia load is:

[0075]

[0076] in, It represents the stress of the pressure casing under vertical inertia load, e1 is a constant, e1=14.28, N z Represents the engine vertical inertia load factor.

[0077] The functional relationship between the aircraft pitch angular velocity and the pressure casing stress under the pitch gyro load is:

[0078]

[0079] in, represents the pressure casing stress under the pitch gyro load, f1 is a constant, f1=8.64, Indicates the aircraft pitch angular velocity.

[0080] The functional relationship between the aircraft yaw angular velocity and the pressure casing stress under the yaw gyro load is:

[0081] σ ψ =g1×ψ

[0082] Among them, σ ψ It represents the stress of the pressure casing under the yaw gyro load, g1 is a constant, g1=8.99, ψ represents the yaw angular velocity of the aircraft.

[0083] Then, based on the functional relationship between different fitting parameters and the corresponding pressure casing stress, the functional relationship between all fitting parameters and the pressure casing equivalent stress is obtained, which can be expressed as:

[0084]

[0085] Among them, σ eqv Indicates the equivalent stress of the pressure casing.

[0086] It can be understood that in step S4, the transient monitorable flight parameters or engine parameters are obtained, which can be directly obtained from the flight parameters and engine parameter recording data under the flight profile, and then combined with the above-mentioned equivalent stress calculation formula, the transient stress of the pressure casing can be quickly calculated.

[0087] In addition, in order to verify the effectiveness and accuracy of the transient stress calculation method of the pressure-bearing casing of the present application, the inventor also conducted an example verification on a combustion chamber casing of an aircraft engine. The load action diagram of the combustion chamber casing of an aircraft engine is shown in the figure below: Figure 3 As shown in Figure 2, the stress distribution results under each independent load are as follows: Figures 4 to 8As shown, the stress distribution results under the yaw gyro load are similar to the stress distribution results under the pitch gyro load, and the stress distribution results under the lateral inertial load are similar to the stress distribution results under the vertical inertial load, so they are not shown separately. Finally, the error between the transient stress result calculated by the fitting formula and the finite element stress analysis result is within 5%, which can meet the needs of engineering applications.

[0088] In addition, if Fig. 9 As shown, another embodiment of the present invention further provides a pressure casing transient stress calculation system, preferably using the pressure casing transient stress calculation method as described above, including:

[0089] Independent load division module, used to conduct independence analysis on the working load of the pressure casing, determine whether there is a correlation between different working loads, and divide the working load into multiple independent loads;

[0090] A fitting parameter determination module, used to determine the fitting parameters corresponding to each independent load;

[0091] Functional relationship fitting module, used to carry out stress analysis on the pressure casing under independent loads based on the fitting parameters corresponding to each independent load, and to fit the functional relationship between different fitting parameters and the corresponding pressure casing stress;

[0092] The transient stress calculation module is used to obtain the transient parameters in the flight mission spectrum, and calculate the transient stress of the pressure casing by combining the functional relationship between all fitting parameters and the equivalent stress of the pressure casing.

[0093] It can be understood that the transient stress calculation system of the pressure casing of the present embodiment first performs an independence analysis on the working load of the pressure casing, divides the working load into multiple independent loads that do not affect each other, and then determines the fitting parameters corresponding to each independent load, so as to perform stress analysis under the independent load based on the fitting parameters, and obtains the functional relationship between different fitting parameters and the corresponding pressure casing stress according to the stress analysis results under the independent load, thereby obtaining the functional relationship between all fitting parameters and the equivalent stress of the pressure casing, and finally obtains the transient parameters in the flight mission spectrum to calculate the transient stress of the pressure casing. The entire calculation process does not require simplification of the flight mission spectrum, and the obtained transient stress is more comprehensive, which can fully reflect the actual transient stress history, and the fitting formula is used to calculate the transient stress, which greatly simplifies the workflow and workload of transient stress calculation, and greatly shortens the transient stress calculation time.

[0094] In addition, another embodiment of the present invention further provides an electronic device, including a processor and a memory, wherein the memory stores a computer program, and the processor executes the steps of the above method by calling the computer program stored in the memory.

[0095] In addition, another embodiment of the present invention further provides a computer-readable storage medium for storing a computer program for calculating transient stress of a pressure casing, wherein the computer program executes the steps of the method described above when running on a computer.

[0096] The general form of computer readable storage media includes: floppy disk, flexible disk, hard disk, magnetic tape, any other magnetic medium, CD-ROM, any other optical medium, punch cards, paper tape, any other physical medium with a pattern of holes, random access memory (RAM), programmable read-only memory (PROM), erasable programmable read-only memory (EPROM), flash erasable programmable read-only memory (FLASH-EPROM), any other memory chip or cartridge, or any other medium that can be read by a computer. The instructions can further be transmitted or received by a transmission medium. The term transmission medium can include any tangible or intangible medium that can be used to store, encode or carry instructions for execution by a machine, and includes digital or analog communication signals or other intangible media that facilitate the communication of the above instructions. Transmission media include coaxial cables, copper wires and optical fibers, which include the wires of a bus used to transmit a computer data signal.

[0097] Those skilled in the art will appreciate that the embodiments of the present application can be provided as methods, systems, or computer program products. Therefore, the present application can adopt the form of complete hardware embodiments, complete software embodiments, or embodiments in combination with software and hardware. Moreover, the present application can adopt the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) that contain computer-usable program code. The scheme in the embodiments of the present application can be implemented in various computer languages, for example, object-oriented programming language Java and literal scripting language JavaScript, etc.

[0098] 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 1A process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0099] 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 comprising 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.

[0100] 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 A step that specifies a function in one or more boxes.

[0101] Although the preferred embodiments of the present application have been described, those skilled in the art may make other changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications falling within the scope of the present application.

[0102] 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.

[0103] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for calculating transient stress of a pressure casing, characterized in that: Includes the following: Conduct independence analysis on the working load of the pressure casing to determine whether there is a correlation between different working loads and divide the working load into multiple independent loads; Determine the fitting parameters corresponding to each independent load; Based on the fitting parameters corresponding to each independent load, the stress analysis of the pressure casing under independent load is carried out, and the functional relationship between different fitting parameters and the corresponding pressure casing stress is fitted, and the functional relationship between different fitting parameters and the corresponding pressure casing stress is summed up to obtain the functional relationship between all fitting parameters and the equivalent stress of the pressure casing; The transient parameters in the flight mission spectrum are obtained, and the transient stress of the pressure casing is calculated by combining the functional relationship between all fitting parameters and the equivalent stress of the pressure casing.

2. The method for calculating transient stress of a pressure casing according to claim 1, characterized in that: Independent loads include temperature loads, gas loads, heading inertial loads, lateral inertial loads, vertical inertial loads, pitch gyro loads, and yaw gyro loads.

3. The method for calculating transient stress of a pressure casing according to claim 2, characterized in that: The fitting parameter corresponding to the temperature load is the engine exhaust temperature, the fitting parameter corresponding to the gas load is the engine intake pressure and the compressor outlet pressure, the fitting parameter corresponding to the heading inertia load is the engine heading inertia load coefficient, the fitting parameter corresponding to the lateral inertia load is the engine lateral inertia load coefficient, the fitting parameter corresponding to the vertical inertia load is the engine vertical inertia load coefficient, the fitting parameter corresponding to the pitch gyro load is the aircraft pitch angular velocity, and the fitting parameter corresponding to the yaw gyro load is the aircraft yaw angular velocity.

4. The method for calculating transient stress of a pressure casing according to claim 3, characterized in that: The functional relationship between the engine exhaust temperature and the pressure casing stress under temperature load is: Among them, σ T It represents the stress of the pressure casing under temperature load, and a1, a2 and a3 are all constants.

5. The method for calculating transient stress of a pressure casing according to claim 3, characterized in that: The functional relationship between the engine inlet pressure and the compressor outlet pressure and the pressure casing stress under gas load is: Among them, σ P represents the pressure casing stress under gas load, b1 and b2 are constants, P3 represents the compressor outlet pressure, and P1 represents the engine inlet pressure.

6. The method for calculating transient stress of a pressure casing according to claim 3, characterized in that: The functional relationship between the engine heading inertia load coefficient and the pressure casing stress under heading inertia load is: in, represents the stress of the pressure casing under the heading inertial load, c1 is a constant, N x Indicates the engine heading inertia load factor.

7. The method for calculating transient stress of a pressure casing according to claim 3, characterized in that: The functional relationship between the engine lateral inertia load coefficient and the pressure casing stress under lateral inertia load is: in, represents the stress of the pressure casing under the lateral inertia load, d1 is a constant, N y Indicates the engine lateral inertia load factor.

8. A pressure casing transient stress calculation system, using the pressure casing transient stress calculation method according to any one of claims 1 to 7, characterized in that: include: Independent load division module, used to conduct independence analysis on the working load of the pressure casing, determine whether there is a correlation between different working loads, and divide the working load into multiple independent loads; A fitting parameter determination module, used to determine the fitting parameters corresponding to each independent load; Functional relationship fitting module, used to carry out stress analysis on the pressure casing under independent loads based on the fitting parameters corresponding to each independent load, and to fit the functional relationship between different fitting parameters and the corresponding pressure casing stress; The transient stress calculation module is used to obtain the transient parameters in the flight mission spectrum, and calculate the transient stress of the pressure casing by combining the functional relationship between all fitting parameters and the equivalent stress of the pressure casing.

9. An electronic device, characterized in that: The method comprises a processor and a memory, wherein the memory stores a computer program, and the processor executes the steps of the method according to any one of claims 1 to 7 by calling the computer program stored in the memory.

10. A computer-readable storage medium for storing a computer program for calculating transient stress of a pressure casing, characterized in that: When the computer program is run on a computer, the steps of the method according to any one of claims 1 to 7 are executed.

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