Method and device for calculating coefficients of elastic motion equation of rocket, terminal equipment and medium

Abstract

The application discloses a kind of rocket elastic motion equation coefficient calculation method, device, terminal equipment and medium, wherein the method includes: according to the mass centroid data of rocket engine at different flight time, the mass point mass data of the engine is calculated;According to the mass point mass data of the engine, generate temporary finite element model file, at least including the rocket related body finite element model of pre-arrangement and the mass point mass data of the engine;According to the body finite element model and the mass point mass data of the engine, the coefficient of the rocket body elastic motion equation is calculated.The rocket inherent characteristics and the coefficient of elastic motion equation can be quickly and conveniently realized by the application.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to a method, apparatus, terminal equipment, and medium for calculating the coefficients of the elastic motion equation of a rocket. Background Technology

[0002] Launch vehicles are non-uniform, continuous elastic bodies with infinitely many degrees of freedom, exhibiting variable stiffness and mass distribution along their longitudinal axis. Under external loads, the rocket body undergoes deformation and bending vibrations, primarily lateral bending vibrations in the slender rocket body. Sensitive elements in the rocket control system detect the additional signals caused by bending deformation, which, through the automatic stabilization device, cause changes in control forces and torques. In severe cases, these additional signals can affect the effective operation of the control system and even lead to rocket flight failure.

[0003] Therefore, the inherent characteristics of the rocket body and the effects of elastic vibration must be considered in the stability design of the rocket control system. Thus, there is an urgent need to propose a scheme for calculating the coefficients of the rocket's inherent characteristics and elastic motion equations. Summary of the Invention

[0004] This application provides a method for calculating the coefficients of the rocket's elastic motion equation, which can quickly and conveniently calculate the coefficients of the rocket's inherent characteristics and elastic motion equation.

[0005] On the one hand, this application provides a method for calculating the coefficients of the elastic motion equation of a rocket through one embodiment of the application, the method comprising:

[0006] Calculate the point mass data of the engine based on the mass centroid data of the rocket engine at different flight times.

[0007] Based on the mass point mass data of the engine, a temporary finite element model file is generated. The temporary finite element model file includes at least a pre-configured rocket body finite element model related to the rocket and the mass point mass data of the engine.

[0008] Based on the finite element model of the rocket body and the mass data of the engine's mass point, the coefficients of the rocket's elastic motion equation are calculated.

[0009] Optionally, calculating the point mass data of the rocket engine based on its center of mass data at different flight times includes:

[0010] Based on the mass centroid data of the rocket engine at different flight times, the particle swarm optimization algorithm is used to iteratively allocate and calculate the mass point mass of the engine to obtain the mass point mass data of the engine.

[0011] Optionally, the step of using a particle swarm optimization algorithm to iteratively allocate and calculate the mass point mass of the engine to obtain the mass point mass data of the engine includes:

[0012] The optimal position of the i-th particle and the optimal position of the particle swarm are searched using the particle swarm algorithm, where i is a positive integer;

[0013] Based on the optimal position of the i-th particle and the optimal position of the particle swarm, the velocity and position of the i-th particle are updated to obtain the optimal velocity and optimal position of the i-th particle.

[0014] The mass point mass data of the engine is calculated based on the optimal velocity and optimal position of the i-th particle.

[0015] Optionally, generating a temporary finite element model file based on the engine's mass point mass data includes:

[0016] The information is read from the pre-stored basic finite element model file to obtain the read information;

[0017] Based on the keywords in the pre-configured file, identify whether the read information is engine quality data;

[0018] If so, the mass point mass data of the engine is updated in the read information, and the updated read information is written into the temporary finite element model file;

[0019] If not, the read information will be directly written into the temporary finite element model file.

[0020] Optionally, the information read is line information read from the basic finite element model file, and the step of generating a temporary finite element model file based on the mass point mass data of the engine further includes:

[0021] Determine whether the last line of information in the basic finite element model file has been read;

[0022] If so, then close the basic finite element model file and the temporary finite element model file;

[0023] If not, repeat the step of identifying whether the read information is engine quality data based on the pre-configured file keywords.

[0024] Optionally, calculating the coefficients of the rocket's elastic motion equation based on the finite element model of the rocket body and the mass point mass data of the engine includes:

[0025] Based on the finite element model of the rocket body and the mass point mass data of the engine, the inherent characteristic data of the rocket are calculated, and the inherent characteristic data includes at least the mode shape data of the rocket body;

[0026] Based on the rocket body vibration mode data and the input rocket parameter data, calculate the coefficients of the rocket body elastic motion equation.

[0027] Optionally, the rocket parameter data includes at least the rocket body mode shape order, and the inherent characteristic data also includes rocket body frequency data. The method further includes:

[0028] The frequency data, mode shape data, and mode shape order of the arrow body are output and displayed.

[0029] On the other hand, this application provides a device for calculating the coefficients of the elastic motion equations of a rocket through one embodiment of this application. The device includes a mass center of mass calculation module, a temporary file generation module, and an equation coefficient calculation module, wherein:

[0030] The mass centroid calculation module is used to calculate the mass point mass data of the rocket engine based on the mass centroid data of the rocket engine at different flight times.

[0031] The temporary file generation module is used to generate a temporary finite element model file based on the mass point mass data of the engine. The temporary finite element model file includes at least a pre-configured rocket body finite element model related to the rocket and the mass point mass data of the engine.

[0032] The equation coefficient calculation module is also used to calculate the elastic motion equation coefficients of the rocket body based on the finite element model of the rocket body and the mass point mass data of the engine.

[0033] For any content not introduced or described in the embodiments of this application, please refer to the relevant descriptions in the foregoing method embodiments; they will not be repeated here.

[0034] On the other hand, this application provides a terminal device through one embodiment of the application. The terminal device includes: a processor, a memory, a communication interface, and a bus; the processor, the memory, and the communication interface are connected through the bus and complete communication with each other; the memory stores executable program code; the processor reads the executable program code stored in the memory to run a program corresponding to the executable program code, so as to execute the method for calculating the coefficients of the rocket elastic motion equation as described above.

[0035] On the other hand, this application provides a computer-readable storage medium through one embodiment of the application, the computer-readable storage medium storing a program that, when the program is run on a terminal device, performs the method for calculating the coefficients of the rocket's elastic motion equation as described above.

[0036] One or more technical solutions provided in this application have at least the following technical effects or advantages: This application calculates the mass point mass data of the rocket engine based on the mass center of mass data of the rocket engine at different flight times; generates a temporary finite element model file based on the mass point mass data of the engine, the temporary finite element model file including at least a pre-configured rocket body finite element model and the mass point mass data of the engine; and calculates the elastic motion equation coefficients of the rocket body based on the rocket body finite element model and the mass point mass data of the engine. In the above solution, this application calculates the elastic motion equation coefficients of the rocket based on the pre-configured rocket body finite element model and the calculated engine mass point mass data. This facilitates the consideration of the inherent characteristics and elastic vibration of the rocket body in the stability design of the rocket control system, which is beneficial to improving the convenience and practicality of calculating the rocket elastic motion equation coefficients, and thus also improves the safety of rocket flight control. Attached Figure Description

[0037] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0038] Figure 1 This is a flowchart illustrating a method for calculating the coefficients of a rocket's elastic motion equation provided in an embodiment of this application.

[0039] Figure 2 This is a schematic diagram of the interface of a computing tool provided in an embodiment of this application.

[0040] Figure 3 This is a flowchart illustrating another method for calculating the coefficients of the rocket's elastic motion equation provided in this application embodiment.

[0041] Figure 4 This is a schematic diagram of the structure of a device for calculating the coefficients of the elastic motion equation of a rocket, provided in an embodiment of this application.

[0042] Figure 5 This is a schematic diagram of the structure of a terminal device provided in an embodiment of this application. Detailed Implementation

[0043] This application provides a method for calculating the coefficients of the rocket's elastic motion equation, which can quickly and conveniently calculate the coefficients of the rocket's inherent characteristics and elastic motion equation.

[0044] The overall idea of ​​the technical solution of this application embodiment is as follows: Calculate the mass point mass data of the rocket engine based on the mass centroid data of the rocket engine at different flight times; generate a temporary finite element model file based on the mass point mass data of the engine, the temporary finite element model file including at least a pre-configured rocket body finite element model related to the rocket and the mass point mass data of the engine; calculate the elastic motion equation coefficients of the rocket body based on the rocket body finite element model and the mass point mass data of the engine.

[0045] To better understand the above technical solutions, the following will provide a detailed explanation of the technical solutions in conjunction with the accompanying drawings and specific implementation methods.

[0046] First, it should be clarified that the term "and / or" in this article is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, or B existing alone. Additionally, the character " / " in this article generally indicates that the preceding and following related objects have an "or" relationship.

[0047] Please see Figure 1 This is a flowchart illustrating a method for calculating the coefficients of a rocket's elastic motion equation provided in an embodiment of this application. Figure 1 The method shown includes the following implementation steps:

[0048] S101. Calculate the mass point mass data of the engine based on the mass center of mass data of the rocket engine at different flight times.

[0049] This application can calculate the mass point mass data of the engine at different flight times based on the mass centroid data of different flight times.

[0050] In practical applications, this application provides a tool for calculating the inherent vibration characteristics and elastic motion equation coefficients of rockets based on development software (such as Matlab or MSc Nastran software, hereinafter referred to as the calculation tool). Users input relevant information through the operation interface provided by the calculation tool, such as the time point to be calculated (i.e., different flight times), the order of the rocket body vibration modes, rocket orbit data, rocket aerodynamic data, rocket mass center of mass data, and the finite element model of the rocket body configured for different stages (specifically, it can exist / represented in the form of a basic rocket body finite element model BDF file), etc. Please refer to... Figure 2 A schematic diagram of the interface of a possible computing tool is shown.

[0051] Understandably, the finite element model of the rocket body used for calculation in this application can be established by Patran. For multi-stage rockets, different finite element models of the rocket body can be established for different stages, which can be established / configured according to actual needs, and this application does not impose any limitations. Furthermore, a mass point model can be established for the rocket engine, and the BDF model file is used as input for modal calculations and input into the MATLAB software. According to the characteristic moments of interest, the corresponding calculation moments are input, i.e., different flight moments of the rocket. It is also necessary to input the rocket aerodynamic data and rocket trajectory data required for calculating the coefficients of the elastic motion equations. At the same time, according to the modes of interest, the calculated rocket mode shape order is input, which can also be called the calculation order or model order, etc.

[0052] S102. Based on the mass point mass data of the engine, generate a temporary finite element model file. The temporary finite element model file includes at least a pre-configured rocket body finite element model related to the rocket and the mass point mass data of the engine.

[0053] In one specific embodiment, this application reads information from a pre-stored basic finite element model (BDF) file, for example, reading information line by line from the BDF file to obtain read information. Then, based on pre-configured file keywords, it identifies whether the read information is engine mass data. If so, the calculated mass point mass data of the engine at the corresponding flight time is updated to the read information, and the updated read information is then written to the temporary finite element model (BDF) file at the corresponding line position. Conversely, if not, the read information can be directly added to the temporary finite element model BDF file at the corresponding line position to obtain the temporary finite element model BDF file.

[0054] S103. Calculate the coefficients of the rocket's elastic motion equation based on the finite element model of the rocket body and the mass data of the engine's mass points.

[0055] In one specific embodiment, this application calculates the inherent characteristic data of the rocket based on the finite element model of the rocket body and the mass point mass data of the engine. The inherent characteristic data may include, but is not limited to, rocket body vibration mode data and rocket body frequency data. Furthermore, the elastic motion equation coefficients of the rocket body can be calculated based on the rocket body vibration mode data and the input rocket parameter data. The rocket parameter data includes, but is not limited to, pre-inputted rocket body vibration mode order, rocket trajectory data, rocket aerodynamic data, and engine mass center of mass data.

[0056] The following describes some specific embodiments involving steps S101-S103.

[0057] In step S101, this application uses the mass centroid data of different flight times as input, combined with the particle swarm optimization algorithm, to iteratively allocate and calculate the mass point mass of the engine, thereby calculating the mass point mass data of the engine at different flight times.

[0058] In the specific implementation, the allocation of engine mass point mass (data) is achieved by the particle swarm optimization algorithm. Its basic principle is: in a D-dimensional target search space, there are N particles forming a swarm. Taking the i-th particle as an example, the relevant content is explained. The i-th particle is represented as a D-dimensional vector, as shown in the following formula (1):

[0059] X i =(x i1 ,x i2 ,...,x iD ), i = 1, 2, ... N Formula (1)

[0060] The velocity of the i-th particle is also represented as a D-dimensional vector, as shown in formula (2) below:

[0061] V i =(v i1 ,v i2 ,...,v iD ), i = 1, 2, ... N Formula (2)

[0062] The optimal position found by the i-th particle is the individual extreme value, denoted by the following formula (3):

[0063] p best =(p i1 ,p i2 ,...p iD ), i = 1, 2, ... N Formula (3)

[0064] The optimal position found by the entire particle swarm is the global extremum, denoted as shown in the following formula (4):

[0065] g best =(g i1 ,g i2 ,...g iD ), i = 1, 2, ... N Formula (4)

[0066] Then according to p best and g best To update the optimal allocation velocity v of the i-th particle id and the optimal allocation position x id The specific formula is shown in formula (5) below:

[0067]

[0068] Where d is 1, 2, ..., D. id Let be the optimal velocity for the i-th particle. W is the inertia factor, specifically a preset non-negative value. C1 and C2 are both learning factors, and r1 and r2 are uniformly random numbers between 0 and 1.

[0069] This application uses particle swarm optimization to randomly solve for the engine's mass centroid data at different flight times, and iteratively finds the optimal allocation value of the engine's mass point mass data.

[0070] For the specific implementation process of step S102, please refer to [link / reference]. Figure 3 As shown. Figure 3 The method for calculating the coefficients of the rocket's elastic motion equations includes the following steps:

[0071] S301. Based on different flight times, use the fopen function to generate and open a blank temporary finite element model (bdf) file.

[0072] S302. Open the base BDF file. This base BDF file should at least include the rocket body finite element model configured for different rocket stages, and may also include pre-stored rocket engine mass point mass data and other information.

[0073] S303. Use the fgetl function to read information from the base BDF file line by line to obtain the read information.

[0074] S304. Based on the pre-configured BDF card keywords, determine whether the read information is engine quality data.

[0075] If the application determines that the read information is engine quality data, it continues to execute step S305; otherwise, it executes step S306.

[0076] S305. The calculated mass point mass data of the engine is rewritten into the mass data in the corresponding row of the read information, and the updated read information is written into a temporary BDF file. In other words, this application can generate the temporary BDF file based on the base BDF file and the calculated mass point mass data of the engine.

[0077] S306. Directly write the read information read line by line from the base bdf file into the temporary bdf file.

[0078] S307. Determine whether the last line of information in the base BDF file has been read.

[0079] If the application determines that the last line of information in the base BDF file has been read, it may continue to execute step S308; otherwise, it may repeat the above steps S303-S306.

[0080] S308. Use the fclose function to close the base BDF file and the temporary BDF file.

[0081] In step S103, after generating / updating the temporary BDF file, this application can call the start DOS function to start the development software (e.g., MSC Nastran software) and calculate the inherent characteristic data of the rocket based on the temporary BDF file, such as rocket body frequency data and rocket body vibration mode data.

[0082] Furthermore, this application calculates the coefficients of the elastic motion equation of the rocket body based on the calculated mode shape data and the input rocket parameter data, such as rocket body aerodynamic data, rocket body trajectory data, rocket engine mass center of mass data, and rocket body mode shape order. Specifically, this application can calculate the corresponding coefficients of the elastic motion equation of the rocket body based on the generalized aerodynamic force and the generalized control force, as follows:

[0083] The generalized aerodynamic force of the equivalent rigid body arrow body, which is proportional to the rotational angular velocity, is expressed by the following formula (6):

[0084]

[0085] The generalized aerodynamic force of the equivalent rigid body arrow body, which is proportional to the angle of attack, is expressed by the following formula (7):

[0086]

[0087] The generalized control force is expressed as shown in the following formula (8):

[0088] Q 3i Py =P y W i (X R ) Formula (8)

[0089] In the above formula, ρ is the atmospheric density, v is the velocity of the rocket body, and S... M It is the characteristic area. X is the derivative of the aerodynamic normal force coefficient, W is the mode shape data of the rocket body, and X is the derivative of the aerodynamic normal force coefficient. T Let X be the coordinates of the center of mass of the entire rocket. n X is the distance from the theoretical cusp. R Let q be the distance from the attitude control engine position to the theoretical apex, and P be the ballistic dynamic pressure. y Here, represents the thrust of the attitude control engine, and ... The parameters are included in the rocket's aerodynamic data, while the remaining parameters are included in the rocket's trajectory data.

[0090] Based on the above generalized aerodynamic force and generalized control force, the coefficients of the elastic motion equation of the arrow body are calculated as shown in the following formula (9):

[0091]

[0092] Among them, M i This refers to the mass of the rocket's body.

[0093] In an optional embodiment, this application may also output the calculated arrow body frequency data, arrow body vibration mode data, and arrow body vibration mode order, and display them to the user for viewing.

[0094] By implementing this application, the application calculates the point mass data of the rocket engine based on the mass center of mass data of the rocket engine at different flight times; generates a temporary finite element model file based on the point mass data of the engine, the temporary finite element model file including at least a pre-configured rocket body finite element model and the point mass data of the engine; and calculates the elastic motion equation coefficients of the rocket body based on the rocket body finite element model and the point mass data of the engine. In the above scheme, this application calculates the elastic motion equation coefficients of the rocket based on the pre-configured rocket body finite element model and the calculated point mass data of the engine. This facilitates the incorporation of the inherent characteristics and elastic vibrations of the rocket body into the stability design of the rocket control system, which improves the convenience and practicality of calculating the elastic motion equation coefficients of the rocket, and thus also improves the safety of rocket flight control.

[0095] Based on the same inventive concept, another embodiment of this application provides a device and terminal equipment corresponding to the calculation method of the rocket elastic motion equation coefficients described in the embodiments of this application.

[0096] Please see Figure 4 This is a schematic diagram of a device for calculating the coefficients of the elastic motion equation of a rocket, provided in an embodiment of this application. Figure 4 The illustrated device 40 includes: a mass centroid calculation module 401, a temporary file generation module 402, and an equation coefficient calculation module 403. Optionally, the device further includes a data input module 404, a rocket body inherent characteristic calculation module 405, and a result output module 406. Wherein:

[0097] The mass centroid calculation module 401 is used to calculate the mass point mass data of the engine based on the mass centroid data of the rocket engine at different flight times.

[0098] The temporary file generation module 402 is used to generate a temporary finite element model file based on the mass point mass data of the engine. The temporary finite element model file includes at least a pre-configured rocket body finite element model related to the rocket and the mass point mass data of the engine.

[0099] The equation coefficient calculation module 403 is used to calculate the elastic motion equation coefficients of the rocket body based on the finite element model of the rocket body and the mass point mass data of the engine.

[0100] Optionally, the data input module 404 is used to input rocket parameter data, which may include, but is not limited to, rocket mode shape order, different flight times, basic BDF file, rocket orbit data, rocket aerodynamic data, and engine mass center of mass data, etc., for use by other modules.

[0101] Optionally, the mass centroid calculation module 401 is specifically used for:

[0102] Based on the mass centroid data of the rocket engine at different flight times, the particle swarm optimization algorithm is used to iteratively allocate and calculate the mass point mass of the engine to obtain the mass point mass data of the engine.

[0103] Optionally, the mass centroid calculation module 401 is specifically used for:

[0104] The optimal position of the i-th particle and the optimal position of the particle swarm are searched using the particle swarm algorithm, where i is a positive integer;

[0105] Based on the optimal position of the i-th particle and the optimal position of the particle swarm, the velocity and position of the i-th particle are updated to obtain the optimal velocity and optimal position of the i-th particle.

[0106] The mass point mass data of the engine is calculated based on the optimal velocity and optimal position of the i-th particle.

[0107] Optionally, the temporary file generation module 402 is specifically used for:

[0108] The information is read from the pre-stored basic finite element model file to obtain the read information;

[0109] Based on the keywords in the pre-configured file, identify whether the read information is engine quality data;

[0110] If so, the mass point mass data of the engine is updated in the read information, and the updated read information is written into the temporary finite element model file;

[0111] If not, the read information will be directly written into the temporary finite element model file.

[0112] Optionally, the read information is the line information read from the basic finite element model file, and the temporary file generation module 402 is specifically used for:

[0113] Determine whether the last line of information in the basic finite element model file has been read;

[0114] If so, then close the basic finite element model file and the temporary finite element model file;

[0115] If not, repeat the step of identifying whether the read information is engine quality data based on the pre-configured file keywords.

[0116] Optionally, the rocket body inherent characteristic calculation module 405 is used to calculate the inherent characteristic data of the rocket based on the rocket body finite element model and the mass point mass data of the engine, wherein the inherent characteristic data includes at least the rocket body vibration mode data;

[0117] The equation coefficient calculation module 403 is specifically used to calculate the inherent characteristic data of the rocket based on the finite element model of the rocket body and the mass point mass data of the engine. The inherent characteristic data includes at least the rocket body vibration mode data.

[0118] Optionally, the rocket parameter data includes at least the rocket body vibration mode order, and the inherent characteristic data also includes rocket body frequency data. The result output module 406 is used to output and display the rocket body frequency data, the rocket body vibration mode data, and the rocket body vibration mode order.

[0119] Please also refer to Figure 5, which is a structural schematic diagram of a terminal device provided in an embodiment of this application. Figure 5 The terminal device 50 shown includes at least one processor 501, a communication interface 502, a user interface 503, and a memory 504. The processor 501, communication interface 502, user interface 503, and memory 504 can be connected via a bus or other means; this embodiment of the invention takes connection via bus 505 as an example.

[0120] Processor 501 can be a general-purpose processor, such as a central processing unit (CPU).

[0121] The communication interface 502 can be a wired interface (e.g., an Ethernet interface) or a wireless interface (e.g., a cellular network interface or a wireless LAN interface) for communicating with other terminals or websites. In this embodiment of the invention, the communication interface 502 is specifically used to acquire input rocket parameter data, etc.

[0122] User interface 503 can specifically be a touch panel, including a touch screen and a touch screen display, used to detect operation commands on the touch panel. User interface 503 can also be a physical button or a mouse. User interface 503 can also be a display screen, used to output and display images or data.

[0123] Memory 504 may include volatile memory, such as random access memory (RAM); memory may also include non-volatile memory, such as read-only memory (ROM), flash memory, hard disk drive (HDD), or solid-state drive (SSD); memory 504 may also include combinations of the above types of memory. Memory 504 is used to store a set of program code, and processor 501 is used to call the program code stored in memory 504 to perform the following operations:

[0124] Calculate the point mass data of the engine based on the mass centroid data of the rocket engine at different flight times.

[0125] Based on the mass point mass data of the engine, a temporary finite element model file is generated. The temporary finite element model file includes at least a pre-configured rocket body finite element model related to the rocket and the mass point mass data of the engine.

[0126] Based on the finite element model of the rocket body and the mass data of the engine's mass point, the coefficients of the rocket's elastic motion equation are calculated.

[0127] Optionally, calculating the point mass data of the rocket engine based on its center of mass data at different flight times includes:

[0128] Based on the mass centroid data of the rocket engine at different flight times, the particle swarm optimization algorithm is used to iteratively allocate and calculate the mass point mass of the engine to obtain the mass point mass data of the engine.

[0129] Optionally, the step of using a particle swarm optimization algorithm to iteratively allocate and calculate the mass point mass of the engine to obtain the mass point mass data of the engine includes:

[0130] The optimal position of the i-th particle and the optimal position of the particle swarm are searched using the particle swarm algorithm, where i is a positive integer;

[0131] Based on the optimal position of the i-th particle and the optimal position of the particle swarm, the velocity and position of the i-th particle are updated to obtain the optimal velocity and optimal position of the i-th particle.

[0132] The mass point mass data of the engine is calculated based on the optimal velocity and optimal position of the i-th particle.

[0133] Optionally, generating a temporary finite element model file based on the engine's mass point mass data includes:

[0134] The information is read from the pre-stored basic finite element model file to obtain the read information;

[0135] Based on the keywords in the pre-configured file, identify whether the read information is engine quality data;

[0136] If so, the mass point mass data of the engine is updated in the read information, and the updated read information is written into the temporary finite element model file;

[0137] If not, the read information will be directly written into the temporary finite element model file.

[0138] Optionally, the information read is line information read from the basic finite element model file, and the step of generating a temporary finite element model file based on the mass point mass data of the engine further includes:

[0139] Determine whether the last line of information in the basic finite element model file has been read;

[0140] If so, then close the basic finite element model file and the temporary finite element model file;

[0141] If not, repeat the step of identifying whether the read information is engine quality data based on the pre-configured file keywords.

[0142] Optionally, calculating the coefficients of the rocket's elastic motion equation based on the finite element model of the rocket body and the mass point mass data of the engine includes:

[0143] Based on the finite element model of the rocket body and the mass point mass data of the engine, the inherent characteristic data of the rocket are calculated, and the inherent characteristic data includes at least the mode shape data of the rocket body;

[0144] Based on the rocket body vibration mode data and the input rocket parameter data, calculate the coefficients of the rocket body elastic motion equation.

[0145] Optionally, the rocket parameter data includes at least the rocket body vibration mode order, and the inherent characteristic data also includes rocket body frequency data. The processor 501 is further configured to:

[0146] The frequency data, mode shape data, and mode shape order of the arrow body are output and displayed.

[0147] Since the terminal device described in this embodiment is the terminal device used to implement the method for calculating the coefficients of the rocket elastic motion equation in this application embodiment, those skilled in the art can understand the specific implementation method and various variations of the terminal device in this embodiment based on the method for calculating the coefficients of the rocket elastic motion equation in this application embodiment. Therefore, how the terminal device implements the method in this application embodiment will not be described in detail here. Any terminal device used by those skilled in the art to implement the information processing method in this application embodiment falls within the scope of protection of this application.

[0148] The technical solutions described in the above embodiments of this application have at least the following technical effects or advantages: This application calculates the mass point mass data of the rocket engine based on the mass center of mass data at different flight times; it generates a temporary finite element model file based on the mass point mass data of the engine, the temporary finite element model file including at least a pre-configured rocket body finite element model and the mass point mass data of the engine; and it calculates the elastic motion equation coefficients of the rocket body based on the rocket body finite element model and the mass point mass data of the engine. In the above solution, this application calculates the rocket's elastic motion equation coefficients based on the pre-configured rocket body finite element model and the calculated engine mass point mass data. This facilitates incorporating the inherent characteristics and elastic vibrations of the rocket body into the stability design of the rocket control system, which improves the convenience and practicality of calculating the rocket's elastic motion equation coefficients, thereby enhancing the safety of rocket flight control.

[0149] Those skilled in the art will understand that embodiments of the present invention can be provided as methods, systems, or computer program products. Therefore, the present invention can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present invention can take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0150] This invention is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart illustrations and / or block diagrams. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0151] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0152] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0153] Although preferred embodiments of the invention have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the invention.

[0154] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

Claims

1. A method for calculating the coefficients of the elastic motion equation of a rocket, characterized in that, The method includes: Calculate the point mass data of the engine based on the mass centroid data of the rocket engine at different flight times. Based on the mass point mass data of the engine, a temporary finite element model file is generated. The temporary finite element model file includes at least a pre-configured rocket body finite element model related to the rocket and the mass point mass data of the engine. Based on the finite element model of the rocket body and the mass point mass data of the engine, calculate the coefficients of the elastic motion equation of the rocket body; The step of generating a temporary finite element model file based on the mass point mass data of the engine includes: The information is read from the pre-stored basic finite element model file to obtain the read information; Based on the keywords in the pre-configured file, identify whether the read information is engine quality data; If so, the mass point mass data of the engine is updated in the read information, and the updated read information is written into the temporary finite element model file; If not, the read information will be directly written into the temporary finite element model file.

2. The method according to claim 1, characterized in that, The calculation of the engine's point mass data based on the rocket engine's center of mass data at different flight times includes: Based on the mass centroid data of the rocket engine at different flight times, the particle swarm optimization algorithm is used to iteratively allocate and calculate the mass point mass of the engine to obtain the mass point mass data of the engine.

3. The method according to claim 2, characterized in that, The step of using a particle swarm optimization algorithm to iteratively allocate and calculate the mass point mass of the engine, resulting in the following mass point mass data: The optimal position of the i-th particle and the optimal position of the particle swarm are searched using the particle swarm algorithm, where i is a positive integer; Based on the optimal position of the i-th particle and the optimal position of the particle swarm, the velocity and position of the i-th particle are updated to obtain the updated optimal velocity and optimal position of the i-th particle. Based on the updated optimal velocity and optimal position of the i-th particle, the mass point mass data of the engine is calculated.

4. The method according to claim 1, characterized in that, The information read is the line information read from the basic finite element model file. The step of generating a temporary finite element model file based on the engine's mass point mass data further includes: Determine whether the last line of information in the basic finite element model file has been read; If so, then close the basic finite element model file and the temporary finite element model file; If not, repeat the step of identifying whether the read information is engine quality data based on the pre-configured file keywords.

5. The method according to claim 1, characterized in that, The calculation of the elastic motion equation coefficients of the rocket body based on the finite element model of the rocket body and the mass point mass data of the engine includes: Based on the finite element model of the rocket body and the mass point mass data of the engine, the inherent characteristic data of the rocket are calculated, and the inherent characteristic data includes at least the mode shape data of the rocket body; Based on the rocket body vibration mode data and the input rocket parameter data, calculate the coefficients of the rocket body elastic motion equation.

6. The method according to claim 5, characterized in that, The rocket parameter data includes at least the rocket body vibration mode order, and the inherent characteristic data also includes rocket body frequency data. The method further includes: The frequency data, mode shape data, and mode shape order of the arrow body are output and displayed.

7. A device for calculating the coefficients of the elastic motion equation of a rocket, characterized in that, The device includes a mass centroid calculation module, a temporary file generation module, and an equation coefficient calculation module, wherein: The mass centroid calculation module is used to calculate the mass point mass data of the rocket engine based on the mass centroid data of the rocket engine at different flight times. The temporary file generation module is used to generate a temporary finite element model file based on the mass point mass data of the engine. The temporary finite element model file includes at least a pre-configured rocket body finite element model related to the rocket and the mass point mass data of the engine. The equation coefficient calculation module is also used to calculate the elastic motion equation coefficients of the rocket body based on the finite element model of the rocket body and the mass point mass data of the engine. The temporary file generation module is also used to read information from the pre-stored basic finite element model file to obtain read information; based on the pre-configured file keywords, it identifies whether the read information is engine mass data; if so, it updates the engine mass point mass data into the read information and writes the updated read information into the temporary finite element model file; if not, it directly writes the read information into the temporary finite element model file.

8. A terminal device, characterized in that, The terminal device includes: a processor, a memory, a communication interface, and a bus; the processor, the memory, and the communication interface are connected through the bus and communicate with each other; the memory stores executable program code; the processor reads the executable program code stored in the memory to run a program corresponding to the executable program code, so as to execute the method for calculating the coefficients of the rocket elastic motion equation as described in any one of claims 1-6.

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a program that, when run on a terminal device, performs the method for calculating the coefficients of the rocket's elastic motion equation as described in any one of claims 1-6.

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