Solid rocket internal and external ballistics integrated optimization method, device, equipment and medium

Abstract

The present application belongs to the field of engine design technology, and relates to a method, device, equipment and medium for optimizing the internal and external trajectories of a solid engine. The method includes: obtaining the design parameters of the solid engine, determining the design variables, optimization objectives and constraints, setting the internal ballistic module and the external ballistic module, and establishing an integrated simulation model of the internal and external ballistics; using optimized Latin hypercube for sampling to obtain an initial sample; according to the internal ballistic parameters of the initial sample and the design parameters of the solid engine, input the internal ballistic module to calculate the engine thrust data; according to the external ballistic parameters of the initial sample and the engine thrust data, input the external ballistic module to calculate the engine ballistic data; according to the initial sample and the engine ballistic data, construct a radial basis proxy model; when it is judged that the radial basis proxy model meets the preset conditions, output the current design variables. The present application can be used to optimize the solid engine in an integrated manner.

Description

Technical Field

[0001] The present application relates to the technical field of engine design, and in particular to a method, device, equipment and medium for integrated optimization of internal and external trajectories of solid engines. Background Art

[0002] As the core of the rocket propulsion system, the solid rocket engine has the characteristics of low cost, fast response, easy storage, simple structure and high reliability. Its design quality and level directly determine the performance of the rocket. Therefore, for the overall design of solid rockets and engines, efficiently designing the rocket engine and optimizing the overall performance of the rocket while reasonably optimizing the rocket stage ratio are the main issues in the actual design process.

[0003] In the prior art, commonly used solid rocket engine design optimization methods are:

[0004] (1) Serial design method based on classical optimization algorithm: In traditional rocket design optimization, classical optimization algorithms such as genetic algorithm or evolutionary algorithm are usually used to optimize the design of each stage of solid engines and the rocket as a whole independently. Then, the two processes of engine optimization design and rocket overall optimization design are iterated repeatedly to obtain the optimal results that simultaneously meet the performance of each stage of engines and the overall rocket.

[0005] (2) Integrated design method based on classical optimization algorithms: Using classical optimization algorithms such as genetic algorithms or evolutionary algorithms, the solid engine and the overall parameters of the rocket are integrated into one design, avoiding repeated iterations between independent design optimization processes. However, due to the limitations of algorithm capabilities and the high computational cost of calling the model during the iterative process, a simplified model is usually used for optimization design.

[0006] However, the above method has the following disadvantages:

[0007] (1) Serial design method based on classical optimization algorithm: In order to reduce the calculation amount of the overall design of the launch vehicle due to the influence of computer performance and optimization algorithm efficiency, the solid engine design is generally not considered, and the solid engines of each stage and the overall rocket are optimized and designed independently. This method can achieve the optimal performance of each engine, but it cannot guarantee the optimal performance of the overall rocket. It is necessary to iterate the two processes of engine optimization design and rocket overall optimization design repeatedly to achieve the optimal results at the same time. The efficiency is low and the cycle is long.

[0008] (2) Integrated design method based on classical optimization algorithm: Due to the limitation of algorithm capability and the high computational cost of calling the model during the iteration process, it is difficult to apply it to time-consuming and high-precision simulation models. The only way is to simplify the rocket or engine model and then perform integrated optimization design. This method usually requires thousands of iterations and is difficult to meet the task of high-precision solid rocket engine design. The computational cost of a single design is unacceptable. Summary of the invention

[0009] Based on this, it is necessary to explain what needs to be explained, such as Figure 4 As shown in the above technical problems, a method, device, equipment and medium for integrated optimization of internal and external ballistics of a solid rocket engine are provided, the internal and external ballistic parameters of the solid rocket engine are coupled for integrated optimization design, and a solid rocket sequence approximate optimization framework is established in combination with an agent model, thereby ensuring the overall optimal performance, reducing calculation time and cost, improving optimization efficiency and quality, and solving the problems of low efficiency of overall parameter optimization design, slow iteration, difficulty in obtaining the optimal overall performance, and the need for continuous iterative optimization between disciplines during the design process for independent serial design of internal and external ballistic disciplines, resulting in a waste of computing resources, and achieving rapid optimization design of the performance of a solid rocket engine that meets the optimal overall performance of the rocket.

[0010] The integrated optimization method of internal and external ballistics of solid rocket includes:

[0011] Obtain the design parameters of the solid rocket motor, determine the design variables, optimization objectives and constraints, set up the internal ballistic module and the external ballistic module, and establish an integrated internal and external ballistic simulation model;

[0012] Use optimized Latin hypercube for sampling to obtain initial samples;

[0013] According to the internal ballistic parameters of the initial sample and the design parameters of the solid engine, the internal ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine thrust data; according to the external ballistic parameters of the initial sample and the engine thrust data, the external ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine ballistic data;

[0014] According to the initial sample and the engine trajectory data, a radial basis function proxy model of design variables, optimization objectives and constraint conditions is constructed; when it is determined that the radial basis function proxy model meets the preset conditions, the current design variables are output.

[0015] In one embodiment, when it is determined that the radial basis proxy model does not meet the preset condition:

[0016] Perform adaptive sampling to obtain the next sample;

[0017] Calculate the next engine thrust data and the next engine trajectory data according to the next sample;

[0018] According to the next sample and the next engine trajectory data, the radial basis function proxy model is reconstructed to obtain the next radial basis function proxy model and make a judgment until the next radial basis function proxy model meets the preset conditions.

[0019] In one embodiment, the design parameters of the solid rocket motor are obtained, the design variables, optimization objectives and constraints are determined, the internal ballistic module and the external ballistic module are set, and the internal and external ballistic integrated simulation model is established, including:

[0020] ;

[0021] In the formula, is the wing length of the solid rocket engine, is the wing inclination angle of the solid rocket, is the wing width of the solid rocket engine, is the circumscribed circle diameter of the solid rocket, It is the throat of the solid rocket engine. is the expansion ratio of the solid rocket, is the length of the cylinder section of the solid rocket, and For two different flight angles of attack, For The corresponding time series, For The corresponding time series, To optimize the goal, is the maximum rocket flight altitude, is the terminal falling speed, is the end angle, is the maximum overload, For the Stage solid rocket length, For the Mass constraints of the first-stage solid rocket.

[0022] In one embodiment, a radial basis proxy model of design variables, optimization objectives, and constraints is constructed based on the initial sample and engine trajectory data, including:

[0023] ;

[0024] In the formula, is the radial basis proxy model, is the number of initial sample points in the initial sample, For the The weight coefficients of the basis functions, is the basis function, is the design variable vector, For the The position vector of the sample points, is the Euclidean distance.

[0025] In one embodiment, adaptive sampling is performed to obtain the next sample, including:

[0026] Perform adaptive sampling to solve the following optimization problem, use the optimal solution of the optimization problem as a new sample point, add the new sample point to the initial sample, and obtain the next sample;

[0027] ;

[0028] ;

[0029] In the formula, is the proxy model of the objective function, is the lower limit of the design variable, is the upper limit of the design variable, is the surrogate model for inequality constraints, is the surrogate model for equality constraints, is the minimum Euclidean distance between the new sample point and the initial sample point, is the distance constraint for the new sample points, and are the coordinates of the sample points.

[0030] In one embodiment, according to the internal ballistic parameters of the initial sample and the design parameters of the solid motor, the internal ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine thrust data, including:

[0031] According to the internal ballistic parameters, combustion surface design parameters and nozzle design parameters of the initial sample, the internal ballistic module of the internal and external ballistic integrated simulation model is input to calculate the thrust data, mass data and working time data of the engine.

[0032] In one embodiment, according to the external ballistic parameters of the initial sample and the engine thrust data, the external ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine ballistic data, including:

[0033] According to the external ballistic parameters of the initial sample and the engine thrust data, the external ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine's range data, terminal velocity data, terminal velocity inclination data and maximum altitude data.

[0034] The integrated internal and external ballistic optimization device of the solid rocket includes:

[0035] The acquisition module is used to obtain the design parameters of the solid rocket engine, determine the design variables, optimization objectives and constraints, set the internal ballistic module and the external ballistic module, and establish an integrated internal and external ballistic simulation model;

[0036] A sampling module, used for sampling using optimized Latin hypercube to obtain an initial sample;

[0037] A calculation module, for inputting the internal ballistics parameters of the initial sample and the design parameters of the solid engine into the internal ballistics module of the internal and external ballistics integrated simulation model to calculate the engine thrust data; and for inputting the external ballistics parameters of the initial sample and the engine thrust data into the external ballistics module of the internal and external ballistics integrated simulation model to calculate the engine ballistic data;

[0038] The output module is used to construct a radial basis proxy model of design variables, optimization objectives and constraints based on the initial sample and engine trajectory data; when it is judged that the radial basis proxy model meets the preset conditions, the current design variables are output.

[0039] A computer device comprises a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, the following steps are implemented:

[0040] Obtain the design parameters of the solid rocket motor, determine the design variables, optimization objectives and constraints, set up the internal ballistic module and the external ballistic module, and establish an integrated internal and external ballistic simulation model;

[0041] Use optimized Latin hypercube for sampling to obtain initial samples;

[0042] According to the internal ballistic parameters of the initial sample and the design parameters of the solid engine, the internal ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine thrust data; according to the external ballistic parameters of the initial sample and the engine thrust data, the external ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine ballistic data;

[0043] According to the initial sample and the engine trajectory data, a radial basis function proxy model of design variables, optimization objectives and constraint conditions is constructed; when it is determined that the radial basis function proxy model meets the preset conditions, the current design variables are output.

[0044] A computer-readable storage medium stores a computer program, which, when executed by a processor, implements the following steps:

[0045] Obtain the design parameters of the solid rocket motor, determine the design variables, optimization objectives and constraints, set up the internal ballistic module and the external ballistic module, and establish an integrated internal and external ballistic simulation model;

[0046] Use optimized Latin hypercube for sampling to obtain initial samples;

[0047] According to the internal ballistic parameters of the initial sample and the design parameters of the solid engine, the internal ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine thrust data; according to the external ballistic parameters of the initial sample and the engine thrust data, the external ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine ballistic data;

[0048] According to the initial sample and the engine trajectory data, a radial basis function proxy model of design variables, optimization objectives and constraint conditions is constructed; when it is determined that the radial basis function proxy model meets the preset conditions, the current design variables are output.

[0049] The above-mentioned solid rocket engine internal and external ballistics integrated optimization method, device, equipment and medium aim at the problems that the overall optimization design efficiency of solid rocket engines is low, the engine design of the conventional serial design process needs to be repeatedly optimized and iterated with the overall rocket design, resulting in a waste of computing resources, and the iteration of the conventional integrated design method is cumbersome. A solid rocket engine internal and external ballistics integrated optimization design method based on sequential approximate optimization considering the coupling of internal and external ballistics is proposed. A high-precision solid rocket and engine model is used to carry out parallel integrated design. By coupling the internal and external ballistics discipline design information, the rapid optimization design of the thrust performance of the solid rocket engine is realized, and the independent iteration between the solid engine and the overall parameters of the rocket is effectively avoided, thereby ensuring the overall performance is optimal, shortening the design cycle, reducing the calculation time and cost, and improving the optimization efficiency and quality. At the same time, a sequential approximate optimization method is adopted, and a radial basis proxy model is established for sequential iterative update. There is no need to simplify the accuracy of the simulation model. On the basis of greatly reducing the simulation time and reducing the simulation cost, the simplification of the simulation model is avoided, and the number of optimization iterations is effectively reduced. Only hundreds of iterations are required to obtain a solution with better performance, further improving the efficiency of solid rocket engine design optimization and the efficiency and quality of algorithm optimization. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] Figure 1 This is an application scenario diagram of a method for optimizing the internal and external trajectories of a solid rocket in one embodiment;

[0051] Figure 2 It is a schematic flow chart of a method for optimizing the internal and external trajectories of a solid rocket in one embodiment;

[0052] Figure 3 It is a flow chart of a method for optimizing the internal and external trajectories of a solid rocket in one embodiment;

[0053] Figure 4 A data flow chart of an integrated internal and external ballistic simulation model in one embodiment;

[0054] Figure 5 1 is a configuration parameter diagram of a solid rocket engine in a specific embodiment, wherein (a) is a front view and (b) is a side view;

[0055] Figure 6 A comparison chart of the range and shooting height results of the optimal ballistic curve of the present method and the prior art method in a specific embodiment;

[0056] Figure 7 A comparison diagram of the time and height results of the optimal trajectory curve of the present method and the prior art method in a specific embodiment;

[0057] Figure 8 A comparison diagram of the time and velocity inclination angle results of the optimal trajectory curve of the present method and the prior art method in a specific embodiment;

[0058] Fig. 9 A comparison diagram of the time and speed results of the optimal trajectory curve of the present method and the prior art method in a specific embodiment;

[0059] Fig.10 A comparison diagram of the time and attack angle results of the optimal trajectory curve of the present method and the prior art method in a specific embodiment;

[0060] Fig.11 A comparison diagram of the time and overload results of the optimal trajectory curve of the present method and the prior art method in a specific embodiment;

[0061] Fig.12 It is a structural block diagram of an integrated internal and external trajectory optimization device for a solid rocket motor in one embodiment;

[0062] Fig.13 FIG. 4 is a diagram showing the internal structure of a computer device in one embodiment. DETAILED DESCRIPTION

[0063] In order to make the purpose, technical solutions and advantages of the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not intended to limit the present application. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work are within the scope of protection of the present application.

[0064] It should be noted that all directional indications in the embodiments of the present application (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0065] In addition, the descriptions of "first", "second", etc. in this application are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of this application, "multiple groups" means at least two groups, such as two groups, three groups, etc., unless otherwise clearly and specifically defined.

[0066] In this application, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0067] In addition, the technical solutions between the various embodiments of the present application can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by this application.

[0068] The solid rocket internal and external trajectory integrated optimization method provided in this application can be applied to Figure 1 In the application scenario diagram shown, the terminal 102 communicates with the server 104 through the network, and the terminal 102 may include but is not limited to various personal computers, laptops, smart phones, tablet computers and portable wearable devices, and the server 104 may be various portal websites, servers corresponding to the backend of the work system, etc.

[0069] The present application provides a method for optimizing the internal and external trajectories of a solid rocket. Figure 2 As shown, in one embodiment, the method is applied to Figure 1 The following is an example of a terminal in the example, including:

[0070] Step 202, obtain the design parameters of the solid rocket motor, determine the design variables, optimization objectives and constraints, set the internal ballistic module and the external ballistic module, and establish an internal and external ballistic integrated simulation model.

[0071] Specifically:

[0072] ;

[0073] In the formula, is the wing length of the solid rocket engine, is the wing inclination angle of the solid rocket, is the wing width of the solid rocket engine, is the circumscribed circle diameter of the solid rocket, It is the throat of the solid rocket engine. is the expansion ratio of the solid rocket, is the length of the cylinder section of the solid rocket, and For two different flight angles of attack, For The corresponding time series, For The corresponding time series, is the optimization target, the optimization target is to maximize the rocket range, is the maximum rocket flight altitude, is the terminal falling speed, is the end angle, is the maximum overload, For the Stage solid rocket length, For the Mass constraints of the first-stage solid rocket.

[0074] Step 204: sampling using optimized Latin hypercube to obtain initial samples.

[0075] In this step, the experimental design method of optimizing Latin hypercube is used to sample in the design space to obtain Sample points A uniform initial sample .

[0076] It should be noted that optimizing Latin hypercube is an existing technology.

[0077] Step 206, according to the internal ballistic parameters of the initial sample and the design parameters of the solid engine, input the internal ballistic module of the internal and external ballistics integrated simulation model to calculate the engine thrust data; according to the external ballistic parameters of the initial sample and the engine thrust data, input the external ballistic module of the internal and external ballistics integrated simulation model to calculate the engine ballistic data.

[0078] Specifically:

[0079] The design parameters of solid rocket engines include: combustion surface design parameters and nozzle design parameters.

[0080] According to the internal ballistic parameters, combustion surface design parameters and nozzle design parameters of the initial sample, the internal ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine's thrust data, mass data and working time data.

[0081] According to the external ballistic parameters of the initial sample and the engine thrust data, the external ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine's range data, terminal velocity data, terminal velocity inclination data and maximum altitude data.

[0082] In this step, the initial sample is , the engine trajectory data is , and get the input relationship ( , ).

[0083] It should be noted that how to calculate engine thrust data and engine trajectory data based on input is an existing technology.

[0084] Step 208, constructing a radial basis function proxy model of design variables, optimization objectives and constraints based on the initial sample and the engine trajectory data; when it is determined that the radial basis function proxy model meets the preset conditions, outputting the current design variables.

[0085] Specifically, based on the initial sample and engine trajectory data, a radial basis function proxy model of design variables, optimization objectives, and constraints is constructed. ,include:

[0086] ;

[0087] In the formula, is the radial basis proxy model, is the number of initial sample points in the initial sample, For the The weight coefficients of the basis functions, is the basis function, is the design variable vector, For the The position vector of the sample points, is the Euclidean distance.

[0088] Since the Gaussian function has good continuity and differentiability, the Gaussian function is used as the kernel function of the basis function in the radial basis proxy model:

[0089] ;

[0090] In the formula, is the kernel function of the basis function, For the The kernel width of the basis function.

[0091] exist Under the known premise, Substitute the sample points into the previous formula to get Unknown number of dimensional linear equations, solving the equations can obtain the weight coefficients of the basis functions .

[0092] When the weight coefficients of the basis function are judged to meet the preset conditions, the design ends and the current design variables are output.

[0093] In this step, when it is determined that the radial basis proxy model does not meet the preset conditions:

[0094] Adaptive sampling is performed to obtain the next sample; based on the next sample, the next engine thrust data and the next engine trajectory data are calculated; based on the next sample and the next engine trajectory data, the radial basis proxy model is reconstructed to obtain the next radial basis proxy model and make a judgment until the next radial basis proxy model meets the preset conditions.

[0095] Specifically, adaptive sampling is performed to obtain the next sample, including:

[0096] Adaptive sampling is performed through an adaptive sampling strategy to solve the following optimization problem, taking the optimal solution of the optimization problem as the new sample point and adding the new sample point to the initial sample In the next sample ;

[0097] ;

[0098] ;

[0099] In the formula, is the proxy model of the objective function, is the lower limit of the design variable, is the upper limit of the design variable, is the surrogate model for inequality constraints, is the surrogate model for equality constraints, is the minimum Euclidean distance between the new sample point and the initial sample point, is the distance constraint of the new sample points, which is taken as the minimum distance between sample points. and are the coordinates of the sample points, is the number of sample points. According to the next sample , calculate the next engine thrust data and the next engine trajectory data ; Update the sample library based on the next sample and the next engine trajectory data , Reconstructing the radial basis proxy model , obtain the next radial basis proxy model and judge until the next radial basis proxy model meets the preset conditions. The preset conditions include: the radial basis proxy model converges or reaches the maximum number of calculation steps. The specific preset conditions can be set according to actual conditions.

[0100] In this embodiment, if Figure 3 As shown in the figure, first, an integrated simulation model and data flow of internal and external ballistics of solid rocket engines are constructed, design inputs and outputs are selected and set, and design variables and value ranges are determined; then, optimized Latin hypercube sampling is used in the design space to obtain initial samples; further, each design variable is input into the integrated simulation model of internal and external ballistics respectively, and when the internal ballistics module of the solid engine completes the internal ballistics simulation and aerodynamic characteristics calculation, the thrust, mass, working time and other data are transferred to the external ballistics module for calculation, and the external ballistics simulation is performed. After completing the integral calculation, the ballistic data such as range, terminal velocity, terminal velocity inclination angle, and maximum height are obtained; in addition, a radial basis model is used to construct a radial basis proxy model of design variables, optimization objectives and constraints, and the convergence condition is judged; finally, points are added according to the selected point adding criterion, and the sample library is continuously iterated and updated until the convergence condition is met or the set number of iterations is reached, and the design variable results are output, and finally a solid rocket engine design scheme that meets the optimal overall performance of the rocket is obtained.

[0101] Need to explain, such as Figure 4 The data flow chart of the integrated internal and external ballistics simulation model shown in the figure shows that when the internal ballistics module and the external ballistics module of the integrated internal and external ballistics simulation model are used to calculate the engine data, the data flow used in the calculation is as follows: the rocket aerodynamic force is estimated by DATCOM for engineering, the combustion surface calculation model is established by the Level Set method, the zero-dimensional internal ballistic model is used for calculation, and Simulink is used to build a 3-degree-of-freedom ballistic model for 3-degree-of-freedom external ballistic simulation.

[0102] The above-mentioned internal and external ballistics integrated optimization method of the solid rocket engine aims at the problems that the overall optimization design efficiency of the solid rocket engine is low, the engine design of the conventional serial design process needs to be repeatedly optimized and iterated with the overall rocket design, resulting in a waste of computing resources, and the iteration of the conventional integrated design method is cumbersome. A design method of internal and external ballistics integrated optimization based on sequential approximate optimization considering the coupling of internal and external ballistics of the solid rocket engine is proposed. A high-precision solid rocket and engine model is used to carry out parallel integrated design. By coupling the internal and external ballistic discipline design information, the rapid optimization design of the thrust performance of the solid rocket engine is realized, and the independent iteration between the solid engine and the overall parameters of the rocket is effectively avoided, thereby ensuring the overall performance is optimal, shortening the design cycle, and reducing the calculation time and cost, and improving the optimization efficiency and quality. At the same time, the sequential approximate optimization method is adopted, and the radial basis proxy model is established for sequential iterative update. There is no need to simplify the accuracy of the simulation model. On the basis of greatly reducing the simulation time and reducing the simulation cost, the simplification of the simulation model is avoided, and the number of optimization iterations is effectively reduced. Only hundreds of iterations are required to obtain a solution with better performance, further improving the efficiency of solid rocket engine design optimization and the efficiency and quality of algorithm optimization.

[0103] It should be understood that although Figure 2 The steps in the flowchart are shown in sequence as indicated by the arrows, but these steps are not necessarily executed in the order indicated by the arrows. Unless otherwise specified in this document, there is no strict order restriction for the execution of these steps, and these steps can be executed in other orders. Moreover, Figure 2 At least part of the steps may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily executed at the same time, but can be executed at different times. The execution order of these sub-steps or stages is not necessarily sequential, but can be executed in turn or alternately with other steps or at least part of the sub-steps or stages of other steps.

[0104] In a specific embodiment, Figure 5 The configuration parameter diagram of the solid rocket engine shown in the figure takes the overall design of a missile solid rocket engine in a certain place as an example. The optimization goal is to maximize the rocket range, and constraints are imposed on the maximum trajectory height, terminal velocity inclination, terminal velocity and maximum overload, as well as on the length, mass and total impulse of the engine. Figure 5 In (a), 1 is the length of the engine cylinder section, 2 is the front wing inclination angle, 3 is the wing length, and 4 is the rear wing inclination angle. Figure 5 In (b), 5 is the diameter of the circumscribed circle and 6 is the wing width.

[0105] The rocket internal and external ballistic parameters are selected as design variables, among which the design parameters of the solid rocket engine and their variation ranges are shown in Table 1.

[0106] Table 1 Design parameters of solid rocket motors and their ranges

[0107]

[0108] Considering the complexity of the problem and the computational cost of sample evaluation, 276 initial sample points were obtained in the design space using optimized Latin hypercube sampling. Each design variable was input into the internal ballistic module and the external ballistic module respectively. After the internal ballistic module completed the calculation, the thrust, mass, working time and other data were input into the external ballistic module. The external ballistic integration was performed. After the calculation was completed, the ballistic data such as range, terminal velocity, terminal velocity inclination, and maximum height were obtained. A radial basis proxy model of design variables, optimization objectives, and constraints was established. According to the selected point addition criteria, the sample library was continuously iterated and updated until the convergence conditions of the radial basis proxy model were met or the predetermined number of iterations was reached. The maximum number of iterative point additions was set to 500, for a total of 1276 calculations.

[0109] For the above optimization problems, the optimization design of the internal and external ballistic integration of solid tactical missiles is carried out according to the established internal and external ballistic integration simulation model and data flow, and the zero-dimensional internal ballistic model and the three-degree-of-freedom external ballistic model are used to calculate the engine combustion chamber pressure, thrust data and ballistic data. Specifically: the developed solid engine simulation calculation software (other methods of the prior art can also be used) is used to calculate the combustion chamber pressure and thrust data, the Runge-Kutta integral is used to program and solve the full ballistics, and the missile aerodynamic parameters are obtained using the Datcom software.

[0110] The optimization results of the design variables of the solid rocket motor are shown in Table 2.

[0111] Table 2 Optimization results of design variables for solid rocket motors

[0112]

[0113] The main design performance indicators of the solid rocket engine are shown in Table 3.

[0114] Table 3 Main design performance indicators of solid rocket motor

[0115]

[0116] The overall performance indicators of the integrated design are shown in Table 4.

[0117] Table 4 Overall performance indicators of integrated design

[0118]

[0119] like Figures 6 to 11As shown, there is a comparison chart of the results of the optimal ballistic curve of the missile designed by the method of the present application (ie, the integrated design scheme) and the prior art method (ie, the serial design scheme).

[0120] Using the serial design scheme of the existing technology, after the engine is ignited, because the average thrust is greater than the internal ballistic simulation thrust, the flight time at a positive angle of attack is relatively short under the altitude constraint.

[0121] However, by adopting the integrated design scheme of the present application method, after the engine is ignited, the thrust is less than the average thrust, and under the same altitude constraint, the flight time at a positive angle of attack is relatively long.

[0122] By comparison, it can be found that the serial design ignores the dynamic characteristics of engine thrust, while the integrated design can directly feed back the changing properties of engine thrust to the external ballistics, thereby optimizing the external ballistics and engine design.

[0123] The optimization results show that compared with the serial design, the integrated design has a 0.92% reduction in mass and a 5.14% increase in range.

[0124] The implementation of the integrated internal and external ballistic optimization design of the present application has a fast optimization speed, a strong optimization capability, saves a lot of time cost, has higher efficiency and performance, can effectively meet the needs of solid rocket engine performance optimization, is conducive to the dynamic optimization distribution of engine energy, and realizes the overall performance improvement of the missile.

[0125] The present application also provides a device for optimizing the internal and external trajectory of a solid rocket motor. Fig.12 As shown, in one embodiment, it includes: an acquisition module 1202, a sampling module 1204, a calculation module 1206 and an output module 1208, wherein:

[0126] The acquisition module 1202 is used to acquire the design parameters of the solid rocket motor, determine the design variables, optimization objectives and constraints, set the internal ballistic module and the external ballistic module, and establish an internal and external ballistic integrated simulation model;

[0127] A sampling module 1204 is used to perform sampling using an optimized Latin hypercube to obtain an initial sample;

[0128] The calculation module 1206 is used to input the internal ballistics parameters of the initial sample and the design parameters of the solid motor into the internal ballistics module of the internal and external ballistics integrated simulation model to calculate the engine thrust data; the external ballistics parameters of the initial sample and the engine thrust data are input into the external ballistics module of the internal and external ballistics integrated simulation model to calculate the engine ballistic data;

[0129] The output module 1208 is used to construct a radial basis proxy model of design variables, optimization objectives and constraints based on the initial sample and engine trajectory data; when it is determined that the radial basis proxy model meets the preset conditions, the current design variables are output.

[0130] For the specific definition of the device for optimizing the internal and external trajectories of a solid rocket, please refer to the definition of the method for optimizing the internal and external trajectories of a solid rocket above, which will not be repeated here. Each module in the above device can be implemented in whole or in part by software, hardware, and a combination thereof. Each of the above modules can be embedded in or independent of a processor in a computer device in the form of hardware, or can be stored in a memory in a computer device in the form of software, so that the processor can call and execute the operations corresponding to each of the above modules.

[0131] In one embodiment, a computer device is provided. The computer device may be a terminal, and its internal structure diagram may be as follows: Fig.13 As shown. The computer device includes a processor, a memory, a network interface, a display screen and an input device connected through a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, a method for optimizing the internal and external trajectories of a solid engine is implemented. The display screen of the computer device can be a liquid crystal display screen or an electronic ink display screen, and the input device of the computer device can be a touch layer covering the display screen, or a key, trackball or touchpad provided on the housing of the computer device, or an external keyboard, touchpad or mouse, etc.

[0132] Those skilled in the art will understand that Fig.13 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine certain components, or have a different arrangement of components.

[0133] In one embodiment, a computer device is provided, including a memory and a processor, wherein the memory stores a computer program, and the processor implements the steps of the method in the above embodiment when executing the computer program.

[0134] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the steps of the method in the above embodiment are implemented.

[0135] Those of ordinary skill in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be implemented by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application may include non-volatile and / or volatile memory. Non-volatile memory may include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory may include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0136] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0137] The above-mentioned embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the present application. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the attached claims.

Claims

1. A method for optimizing the internal and external trajectories of a solid rocket, characterized in that: include: Obtain the design parameters of the solid rocket motor, determine the design variables, optimization objectives and constraints, set up the internal ballistic module and the external ballistic module, and establish an integrated internal and external ballistic simulation model; Obtain the design parameters of the solid rocket motor, determine the design variables, optimization objectives and constraints, set up the internal ballistic module and the external ballistic module, and establish an integrated internal and external ballistic simulation model, including: In the formula, is the wing length of the solid rocket engine, is the wing inclination angle of the solid rocket, is the wing width of the solid rocket engine, is the circumscribed circle diameter of the solid rocket, It is the throat of the solid rocket engine. is the expansion ratio of the solid rocket, is the length of the cylinder section of the solid rocket, and For two different flight angles of attack, For The corresponding time series, For The corresponding time series, To optimize the goal, is the maximum rocket flight altitude, is the terminal falling speed, is the end angle, is the maximum overload, For the Stage solid rocket length, For the Stage solid rocket mass constraints; Use optimized Latin hypercube for sampling to obtain initial samples; According to the internal ballistic parameters of the initial sample and the design parameters of the solid engine, the internal ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine thrust data; according to the external ballistic parameters of the initial sample and the engine thrust data, the external ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine ballistic data; according to the internal ballistic parameters of the initial sample and the design parameters of the solid engine, the internal ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine thrust data, including: according to the internal ballistic parameters of the initial sample, the combustion surface design parameters and the nozzle design parameters, the internal ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine thrust data, mass data and working time data; according to the external ballistic parameters of the initial sample and the engine thrust data, the external ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine ballistic data, including: according to the external ballistic parameters of the initial sample and the engine thrust data, the external ballistic module of the internal and external ballistic integrated simulation model is input to calculate the engine range data, terminal velocity data, terminal velocity inclination angle data and maximum height data; According to the initial sample and the engine trajectory data, a radial basis function proxy model of design variables, optimization objectives and constraint conditions is constructed; when it is determined that the radial basis function proxy model meets the preset conditions, the current design variables are output.

2. The method for optimizing the internal and external trajectories of a solid rocket according to claim 1, characterized in that: When it is determined that the radial basis proxy model does not meet the preset conditions: Perform adaptive sampling to obtain the next sample; Calculate the next engine thrust data and the next engine trajectory data according to the next sample; According to the next sample and the next engine trajectory data, the radial basis function proxy model is reconstructed to obtain the next radial basis function proxy model and make a judgment until the next radial basis function proxy model meets the preset conditions.

3. The method for optimizing the internal and external trajectories of a solid rocket according to claim 2, characterized in that: Based on the initial sample and engine trajectory data, a radial basis function proxy model of design variables, optimization objectives, and constraints is constructed, including: In the formula, is the radial basis proxy model, is the number of initial sample points in the initial sample, For the The weight coefficients of the basis functions, is the basis function, is the design variable vector, For the The position vector of the sample points, is the Euclidean distance.

4. The method for optimizing the internal and external trajectories of a solid rocket according to claim 3, characterized in that: Perform adaptive sampling to obtain the next sample, including: Perform adaptive sampling to solve the following optimization problem, use the optimal solution of the optimization problem as a new sample point, add the new sample point to the initial sample, and obtain the next sample; In the formula, is the proxy model of the objective function, is the lower limit of the design variable, is the upper limit of the design variable, is the surrogate model for inequality constraints, is the surrogate model for equality constraints, is the minimum Euclidean distance between the new sample point and the initial sample point, is the distance constraint for the new sample points, and are the coordinates of the sample points.

5. An integrated internal and external trajectory optimization device for a solid rocket motor, characterized in that: include: The acquisition module is used to obtain the design parameters of the solid rocket engine, determine the design variables, optimization objectives and constraints, set the internal ballistic module and the external ballistic module, and establish an integrated internal and external ballistic simulation model; Obtain the design parameters of the solid rocket motor, determine the design variables, optimization objectives and constraints, set up the internal ballistic module and the external ballistic module, and establish an integrated internal and external ballistic simulation model, including: In the formula, is the wing length of the solid rocket engine, is the wing inclination angle of the solid rocket, is the wing width of the solid rocket engine, is the circumscribed circle diameter of the solid rocket, It is the throat of the solid rocket engine. is the expansion ratio of the solid rocket, is the length of the cylinder section of the solid rocket, and For two different flight angles of attack, For The corresponding time series, For The corresponding time series, To optimize the goal, is the maximum rocket flight altitude, is the terminal falling speed, is the end angle, is the maximum overload, For the Stage solid rocket length, For the Stage solid rocket mass constraints; A sampling module, used for sampling using optimized Latin hypercube to obtain an initial sample; A calculation module, for inputting the internal ballistics module of the internal and external ballistics integrated simulation model according to the internal ballistics parameters of the initial sample and the design parameters of the solid engine to calculate the engine thrust data; inputting the external ballistics module of the internal and external ballistics integrated simulation model according to the external ballistics parameters of the initial sample and the engine thrust data to calculate the engine ballistic data; inputting the internal ballistics module of the internal and external ballistics integrated simulation model according to the internal ballistics parameters of the initial sample and the design parameters of the solid engine to calculate the engine thrust data, including: inputting the internal ballistics module of the internal and external ballistics integrated simulation model according to the internal ballistics parameters of the initial sample, the combustion surface design parameters and the nozzle design parameters to calculate the engine thrust data, mass data and working time data; inputting the external ballistics module of the internal and external ballistics integrated simulation model according to the external ballistics parameters of the initial sample and the engine thrust data to calculate the engine ballistic data, including: inputting the external ballistics module of the internal and external ballistics integrated simulation model according to the external ballistics parameters of the initial sample and the engine thrust data to calculate the engine range data, terminal velocity data, terminal velocity inclination angle data and maximum height data; The output module is used to construct a radial basis proxy model of design variables, optimization objectives and constraints based on the initial sample and engine trajectory data; when it is judged that the radial basis proxy model meets the preset conditions, the current design variables are output.

6. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 4 are implemented.

7. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 4 are implemented.

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