CN108170963A - The automation computational methods and device of solid-liquid rocket flight reappearance characteristic - Google Patents

Abstract

The present invention provides the automation computational methods and device of a kind of solid-liquid rocket flight reappearance characteristic, are related to computer realm, with alleviate heavy workload in the prior art, it is inefficient the technical issues of.This method is simple and efficient, can accurately realize that result exports, improve user experience.This method includes：Receive parameter information input by user；Wherein, the parameter information includes solid-liquid engine fuel burning data file and rocket structure parameter；The quality center of mass performance data of the entire flight course of solid-liquid rocket is generated according to the parameter information；The quality center of mass performance data is exported.

Description

Automatic calculation method and device for flight mass characteristics of solid-liquid rocket

technical field

The invention relates to the technical field of data processing, in particular to an automatic calculation method and device for the flight quality characteristics of a solid-liquid rocket.

Background technique

The overall design of the rocket is a process of comprehensively considering various factors and satisfying multiple performance indicators, and the analysis of the overall mass characteristics of the rocket, especially the calculation of the center of mass and moment of inertia, is one of the most important tasks. After designing the structural shape of the rocket and determining the installation equipment and engine parameters, it is necessary to carry out the flight aerodynamic simulation of the rocket according to the actual situation and the changes in the mass characteristics of the rocket during flight, and then match the control system. Therefore, it is necessary to calculate the mass characteristics of the entire flight process for the rocket that has been designed. Since the solid-liquid engine involves a tank containing a liquid oxidant, a gas cylinder containing gas, etc., the calculation of the flight mass characteristics of a solid-liquid rocket is more complicated, and there are more factors to be considered.

In the current overall rocket design, the design of the rocket often needs to be iterated many times, and the workload is very heavy. At present, there is a lack of an effective and fast calculation method for the mass characteristics of solid-liquid rockets, and there is also a lack of efficient and convenient calculation tools, which leads to low efficiency in the iterative process of solid-liquid rocket design.

For the above problems, there is no effective solution at present.

Contents of the invention

In view of this, the purpose of the present invention is to provide an automatic calculation method and device for the flight mass characteristics of solid-liquid rockets, so as to alleviate the technical problems of heavy workload and low efficiency in the prior art.

In the first aspect, an embodiment of the present invention provides an automatic calculation method for the flight mass characteristics of a solid-liquid rocket, including:

Receive parameter information input by the user; wherein, the parameter information includes solid-liquid engine fuel combustion data files and rocket structure parameters;

Generating mass center characteristic data of the solid-liquid rocket throughout the flight process according to the parameter information;

Outputting the mass centroid characteristic data.

With reference to the first aspect, the embodiment of the present invention provides a first possible implementation manner of the first aspect, wherein the outputting the mass centroid characteristic data specifically includes:

Writing the characteristic data of the mass center of mass into an automatically generated form according to a preset format to generate a data table file;

Save the generated data table file in the specified location;

and / or,

generating a variation curve according to the mass centroid characteristic data;

Output the change curve to the display interface.

In combination with the first aspect, the embodiment of the present invention provides a second possible implementation manner of the first aspect, wherein the generating the mass centroid characteristic data of the solid-liquid rocket throughout the flight process according to the parameter information specifically includes:

Using the gas cylinder calculation model to calculate the first mass center of mass characteristic data of the gas cylinder system according to the initial pressure and mass of the gas cylinder in the parameter information;

Using the calculation model of the oxidant storage tank to calculate the second mass centroid characteristic data of the storage tank system according to the flow rate of the oxidant in the parameter information;

Use the combustion chamber calculation model to calculate according to the ground test data in the parameter information, and obtain the third mass centroid characteristic data of the combustion chamber system;

The first mass center characteristic data, the second mass characteristic data and the third mass characteristic data are calculated to generate the mass center of mass characteristic data of the solid-liquid rocket throughout the flight process.

With reference to the second possible implementation manner of the first aspect, the embodiment of the present invention provides a third possible implementation manner of the first aspect, wherein the method further includes:

The oxidant storage tank, gas cylinder and combustion chamber were reasonably simplified, and the calculation models of the oxidant storage tank, gas cylinder and combustion chamber were constructed.

In combination with the third possible implementation of the first aspect, the embodiment of the present invention provides a fourth possible implementation of the first aspect, wherein the oxidant storage tank, the gas cylinder and the combustion chamber are reasonably simplified respectively , to construct the calculation model of the oxidant storage tank, gas cylinder and combustion chamber, including:

In order to simplify the calculation process, the following basic assumptions are made:

In the gas cylinder calculation part, it is assumed that the gas in the gas cylinder is a cylinder, and the outer diameter changes uniformly inward;

For the calculation part of the oxidant storage tank, it is assumed that the hydrogen peroxide in the storage tank is a cylinder, and the outer diameter changes uniformly inward, and the liquid bag model of the storage tank is simplified as a 2mm thick sleeve;

In the calculation part of the combustion chamber, it is assumed that the charge column of the solid-liquid engine is a single-hole cylinder, only the inner hole burns, and the charge surface retreats uniformly;

Based on the above basic assumptions, the corresponding oxidant storage tank calculation models, gas cylinder calculation models and combustion chamber calculation models are respectively established.

In the second aspect, an embodiment of the present invention provides an automatic calculation device for the flight quality characteristics of a solid-liquid rocket, including:

The information input module is used to receive parameter information input by the user; wherein, the parameter information includes solid-liquid engine fuel combustion data files and rocket structure parameters;

A calculation module, configured to generate mass center-of-mass characteristic data of the solid-liquid rocket throughout the flight process according to the parameter information;

An output module, configured to output the mass centroid characteristic data.

With reference to the second aspect, the embodiment of the present invention provides a first possible implementation manner of the second aspect, wherein the information input module includes a first input module and a second input module;

The first input module is used to receive the rocket structure parameters input by the user; wherein, the first input module includes a structural mass window, a structural center of mass window, a moment of inertia Ix window, a moment of inertia Iy window, an oxidant parameter window, a gas cylinder pressure window, full arrow length window;

The second input module is used for receiving the solid-liquid engine fuel combustion data file input by the user.

With reference to the second aspect, the embodiment of the present invention provides a second possible implementation manner of the second aspect, wherein the output module includes a first output module and a second output module;

The first output module is used to write the mass center of mass characteristic data into an automatically generated form according to a preset format to generate a data table file; save the generated data table file in a designated location;

The second output module is used to generate a change curve according to the mass centroid characteristic data; and output the change curve to a display interface.

In combination with the second aspect, the embodiment of the present invention provides a third possible implementation manner of the second aspect, wherein the device further includes:

The learning module is used to reasonably simplify the parts of the oxidant storage tank, gas cylinder and combustion chamber, and construct the calculation model of the oxidant storage tank, gas cylinder and combustion chamber. With reference to the third possible implementation manner of the second aspect, the embodiment of the present invention provides a fourth possible implementation manner of the second aspect, wherein the computing module is specifically configured to:

Using the gas cylinder calculation model to calculate the first mass center of mass characteristic data of the gas cylinder system according to the initial pressure and mass of the gas cylinder in the parameter information;

Using the calculation model of the oxidant storage tank to calculate the second mass centroid characteristic data of the storage tank system according to the flow rate of the oxidant in the parameter information;

Use the combustion chamber calculation model to calculate according to the ground test data in the parameter information, and obtain the third mass centroid characteristic data of the combustion chamber system;

The first mass center characteristic data, the second mass characteristic data and the third mass characteristic data are calculated to generate the mass center of mass characteristic data of the solid-liquid rocket throughout the flight process.

In the third aspect, the embodiment of the present invention also provides an electronic device, including a memory and a processor, the memory stores a computer program that can run on the processor, and when the processor executes the computer program, the computer program is implemented. The steps of the method described in the first aspect above.

In a fourth aspect, an embodiment of the present invention further provides a computer-readable medium having a non-volatile program code executable by a processor, and the program code causes the processor to execute the method described in the first aspect above.

Embodiments of the present invention bring the following beneficial effects:

In the automatic calculation method of the flight quality characteristics of solid-liquid rockets provided in the embodiments of the present invention, firstly by receiving the parameter information input by the user; wherein, the parameter information includes solid-liquid engine fuel combustion data files and rocket structure parameters; then according to the above parameters The information generates the characteristic data of the center of mass of the solid-liquid rocket during the entire flight process; finally, the above-mentioned characteristic data of the center of mass of the solid-liquid rocket is output. Therefore, the technical solution provided by the embodiment of the present invention can quickly and accurately calculate the flight process of the solid-liquid rocket to obtain the characteristic data of the center of mass of the whole mass by inputting parameters, which can alleviate the problems of heavy workload and low efficiency in the prior art. question. In addition, the characteristic data of the center of mass of the solid-liquid rocket obtained during the flight process can also provide necessary data for aerodynamic calculation and control system design. The method is simple and convenient, can accurately realize the output of results, and improves the user experience. At the same time, the automatic calculation method of the flight quality characteristics of the solid-liquid rocket has a theoretical basis, strong applicability, and high reliability.

Additional features and advantages of the invention will be set forth in the description which follows, and in part will be apparent from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.

In order to make the above-mentioned objects, features and advantages of the present invention more comprehensible, preferred embodiments will be described in detail below together with the accompanying drawings.

Description of drawings

In order to more clearly illustrate the specific implementation of the present invention or the technical solutions in the prior art, the following will briefly introduce the accompanying drawings that need to be used in the specific implementation or description of the prior art. Obviously, the accompanying drawings in the following description The drawings show some implementations of the present invention, and those skilled in the art can obtain other drawings based on these drawings without any creative work.

Fig. 1 is a schematic flow chart of an automatic calculation method for the flight quality characteristics of a solid-liquid rocket provided by an embodiment of the present invention;

FIG. 2 is a schematic diagram of step S102 in FIG. 1;

Fig. 3 is a schematic flow chart of another automatic calculation method for the flight mass characteristics of a solid-liquid rocket provided by an embodiment of the present invention;

4 is a schematic diagram of an automatic calculation device for the flight quality characteristics of a solid-liquid rocket provided by an embodiment of the present invention;

5 is a detailed schematic diagram of an automatic calculation device for the flight quality characteristics of a solid-liquid rocket provided by an embodiment of the present invention;

6 is a schematic diagram of an interface of an automatic calculation device for the flight quality characteristics of a solid-liquid rocket provided by an embodiment of the present invention;

Fig. 7 is the automatic calculation flow chart of the automatic calculation device for the flight quality characteristics of solid-liquid rockets provided by the embodiment of the present invention;

FIG. 8 is a schematic structural diagram of an electronic device provided by an embodiment of the present invention.

Detailed ways

In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, not all of them. the embodiment. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

In the current overall rocket design, the design of the rocket often needs to be iterated many times, and the workload is very heavy. At present, there is a lack of an effective and fast calculation method for the mass characteristics of solid-liquid rockets, and there is also a lack of efficient and convenient calculation tools, which leads to low efficiency in the iterative process of solid-liquid rocket design. Based on this, the embodiment of the present invention provides an automatic calculation method and electronic equipment for the flight mass characteristics of a solid-liquid rocket, which can alleviate the problems of large calculation and low efficiency in the prior art.

In order to facilitate the understanding of this embodiment, an automatic calculation method for the flight mass characteristics of a solid-liquid rocket disclosed in the embodiment of the present invention is firstly introduced in detail.

Embodiment one:

Fig. 1 shows a schematic flowchart of an automatic calculation method for the flight mass characteristics of a solid-liquid rocket provided by an embodiment of the present invention. Referring to Fig. 1, the automatic calculation method of the solid-liquid rocket flight mass characteristics can be applied to the field of solid-liquid rocket design, and the method includes the following steps:

Step S101: Receive parameter information input by the user; wherein, the above parameter information includes solid-liquid engine fuel combustion data files and rocket structure parameters.

The rocket structural parameters here include information such as the structure and engine parameters of the solid-liquid rocket. Specifically, the rocket structural parameters include the actual pure structural mass of the solid-liquid rocket, the position of the center of mass of the pure structural part of the rocket, and the axial direction of the pure structural part of the solid-liquid rocket. The moment of inertia of the solid-liquid rocket, the moment of inertia of the vertical axis of the pure structural part of the solid-liquid rocket, the parameters of the oxidizer, the initial pressure of the actual gas cylinder of the solid-liquid rocket, and the initial full arrow length of the solid-liquid rocket. Among them, the oxidant parameters include the quality of the oxidant, the large flow, the working time of the large flow and the small flow. It should be noted that the above oxidant parameters are specifically input according to design requirements.

The fuel combustion data files of solid-liquid engines can be imported by means of file retrieval. In one embodiment, the solid-liquid engine fuel combustion data file can be searched by the user clicking the browse button on the right, for example, the designed solid-liquid engine combustion test data is imported into the program in the form of an Excel table. It should be pointed out that the user can import data from any location in the local computer, and the path and file name will be displayed in the left window for user inspection.

Step S102: Generate mass centroid characteristic data of the solid-liquid rocket throughout the flight process according to the above parameter information.

Specifically, referring to FIG. 2, the step S102 is mainly realized through the following steps:

S1021: Using the gas cylinder calculation model to calculate the first mass centroid characteristic data of the gas cylinder system according to the initial pressure and mass of the gas cylinder in the parameter information.

Wherein, the first characteristic data of the center of mass includes the gas mass in the gas cylinder, the center of mass of the gas cylinder, and the moment of inertia of the center of mass of the gas cylinder.

S1022: Using the calculation model of the oxidant storage tank to calculate and obtain the second mass centroid characteristic data of the storage tank system according to the flow rate of the oxidant in the parameter information.

Wherein, the second characteristic data of the mass center of mass includes the gas mass in the tank, the overall mass of the tank, the center of mass of the tank, and the moment of inertia of the center of mass of the tank.

S1023: Using the combustion chamber calculation model to perform calculations based on the ground test data in the parameter information, to obtain the third mass centroid characteristic data of the combustion chamber system.

Wherein, the third mass center characteristic data includes the overall mass of the combustion chamber (including the mass of fuel and oxidant), the mass center of the combustion chamber and the moment of inertia of the combustion chamber mass center.

S1024: Calculate the above-mentioned first mass characteristic data, second mass characteristic data and third mass characteristic data to generate mass centroid characteristic data of the solid-liquid rocket during the whole flight process.

It should be noted that the calculation model of the oxidant storage tank, the gas cylinder and the combustion chamber mentioned above are constructed by rationally simplifying the oxidant storage tank, gas cylinder and combustion chamber respectively.

S1021, S1022, and S1023 here are used for convenience of description only, and do not represent their sequence. For example, S1021, S1022, and S1023 can be performed simultaneously or in any permutation and combination order.

Therefore, before the step S102, the method also includes the step of establishing a calculation model:

That is, the oxidant storage tank, gas cylinder and combustion chamber are reasonably simplified, and the calculation model of the oxidant storage tank, gas cylinder and combustion chamber are constructed.

The step of establishing a calculation model is mainly realized in the following ways:

In order to simplify the calculation process, the following basic assumptions are made:

In the gas cylinder calculation part, it is assumed that the gas in the gas cylinder is a cylinder, and the outer diameter changes uniformly inward.

In the calculation part of the oxidant storage tank, it is assumed that the hydrogen peroxide in the storage tank is a cylinder, and the outer diameter changes uniformly inward, and the liquid sac model of the storage tank is simplified as a 2mm thick sleeve.

In the calculation part of the combustion chamber, it is assumed that the grain of the solid-liquid engine is a single-hole cylinder, only the inner hole burns, and the grain surface retreats uniformly.

Based on the above basic assumptions, the corresponding oxidant storage tank calculation models, gas cylinder calculation models and combustion chamber calculation models are respectively established.

Specifically, according to the above-mentioned basic assumptions and relatively mature rocket design formulas such as the cylinder rotational inertia formula and the inertia translation law, the corresponding calculation models of the oxidant storage tank, gas cylinder and combustion chamber are respectively established.

Step S103: Output the above-mentioned mass centroid characteristic data.

During specific implementation, this step S103 can be realized in the following ways:

Method A:

A1 Write the above-mentioned mass centroid characteristic data into the automatically generated table according to the preset format to generate a data table file.

Among them, the preset format is a standard format that pre-defines the unit and size of each data and the output order of each data. The table is a multi-row multi-column table corresponding to the preset format, so as to facilitate data filling in the table. Generate data table files. The form of the data sheet is concise and can be conveniently used directly. Automate the work of extracting data and improve the operation efficiency of users (such as computing personnel).

In actual implementation, automatically create and generate an Excel table in the required format, and at the same time write the calculated data into the table according to the format, and finally directly obtain the data table in the required format, which automates the work of extracting data and improves efficiency.

A2 saves the generated data table file in the specified location.

The generated data table file can be stored in a specified location according to the path set by the user. Specifically, the generated data table file is saved in the same folder as the input file.

and / or;

Method B:

B1 generates a change curve according to the above-mentioned mass centroid characteristic data.

Among them, the above-mentioned change curves include the first change curve (mass data and time relationship curve), the second change curve (mass center data and time relationship curve), the third change curve (axial moment of inertia data and time relationship curve), the fourth change curve Variation curve (vertical axial moment of inertia data and time relationship curve); the first variation curve, the second variation curve, the third variation curve, and the fourth variation curve respectively reflect the mass data, center of mass data, axial Moment of inertia data, vertical axis moment of inertia data change with time.

Specifically, according to the characteristic data of the center of mass of the rocket, the flight mass, the position of the center of mass, the moment of inertia in the axial direction, and the moment of inertia in the vertical axis are plotted along with the flight time.

B2 outputs the above change curve to the display interface.

The display interface here may be a screen of a display device or a projection device, or may be a graphic display interface of software.

Specifically, the change curve is output to the display screen, and displayed to the user through a graphical display interface, which is convenient for the user to perform an intuitive preliminary inspection and analysis on the result.

The automatic calculation method of the flight mass characteristics of solid-liquid rockets provided by the embodiments of the present invention first receives parameter information input by the user; wherein, the parameter information includes solid-liquid engine fuel combustion data files and rocket structure parameters; and then generates according to the above parameter information The center-of-mass characteristic data of the solid-liquid rocket during the entire flight; finally, the above-mentioned characteristic data of the center-of-mass characteristic is output. Therefore, the technical scheme that the embodiment of the present invention provides, establishes mathematical model on the basis of solid-liquid rocket theoretical analysis, and application computer software (such as matlab) carries out programming, and can show GUI interface to user; Above-mentioned GUI interface includes parameter Input area, output result area and graph drawing area; by inputting parameters, the flight process of the solid-liquid rocket can be quickly and accurately calculated to obtain the overall mass center of mass characteristic data, that is, by receiving the parameters input by the user, use the constructed mathematical model to analyze and solve , automatically generating results and outputting the generated results, alleviating the problems of heavy workload and low efficiency in the prior art. In addition, the characteristic data of the center of mass of the solid-liquid rocket obtained during the flight process can also provide necessary data for aerodynamic calculation and control system design. The method is simple and convenient, can accurately realize the output simulation, and improves the user experience. At the same time, the automatic calculation method of the flight quality characteristics of the solid-liquid rocket has a theoretical basis, strong applicability, and high reliability.

Embodiment two:

As shown in Figure 3, on the basis of Embodiment 1, the embodiment of the present invention provides another automatic calculation method for the flight quality characteristics of the solid-liquid rocket. Before step S102, the automatic calculation method for the flight quality characteristics of the solid-liquid rocket Also includes:

Step S201: Determine whether the above parameter information overflows.

The overflow includes that the parameter information input by the user is not within the preset parameter range or some parameters in the parameter information do not meet the boundary conditions or the input format is wrong.

If so, that is, when the above parameter information is overflowing, execute step S202: prompting error information and a suggested solution.

Wherein, the error information includes information such as numerical error, unit error, and file error; the suggestion solution may be re-input, or it may be suggested to expand or reduce the value size.

If not, that is, when the above parameter information does not overflow, step S102 is executed.

By judging whether the parameter overflows, subsequent invalid calculations can be prevented, user time is saved, and efficiency is improved.

Embodiment three:

As shown in Figure 4 and Figure 5, the automatic calculation device for the flight quality characteristics of the solid-liquid rocket provided by the embodiment of the present invention, the automatic calculation device for the flight quality characteristics of the solid-liquid rocket includes:

The information input module 100 is configured to receive parameter information input by the user; wherein, the parameter information includes solid-liquid engine fuel combustion data files and rocket structure parameters.

The calculation module 200 is configured to generate mass centroid characteristic data of the solid-liquid rocket during the entire flight process according to the parameter information.

The output module 300 is configured to output the characteristic data of the centroid of mass.

Further, the information input module 100 includes a first input module 101 and a second input module 102 .

The first input module 101 is also called the rocket structure parameter input module, and is used to receive the rocket structure parameters input by the user; wherein, the first input module includes a structural mass window, a structural center of mass window, a moment of inertia Ix window, and a moment of inertia Iy window , oxidant parameter window, gas cylinder pressure window, full arrow length window. The windows are arranged sequentially from top to bottom, and there are notes on the filled content on the left side of the window.

Specifically, the content of the rocket parameter input module is:

The Structural Mass window is used to receive user input (filled in) the actual pure structural mass of the solid-liquid rocket. Among them, the actual pure structural mass of the solid-liquid rocket can be directly calculated by drawing software (such as Inventor, Solidworks) according to the three-dimensional model of the solid-liquid rocket. Specifically, the drawing software uses Inventor.

The Structural Centroid window is used to receive the position of the center of mass of the purely structural part of the rocket input by the user. Among them, the position of the center of mass of the pure structural part of the rocket can be directly calculated by drawing software based on the three-dimensional model of the solid-liquid rocket and the bottom end of the rocket as the reference plane.

The moment of inertia Ix window is used to receive the moment of inertia of the pure structural part of the solid-liquid rocket along the axis input by the user. Among them, the moment of inertia along the axial direction of the pure structural part of the solid-liquid rocket here can be directly calculated by drawing software based on the three-dimensional model of the solid-liquid rocket.

The moment of inertia Iy window is used to receive the moment of inertia of the vertical axis of the pure structural part of the solid-liquid rocket input by the user. Here, the moment of inertia of the pure structural part of the solid-liquid rocket in the vertical axis can be directly calculated by drawing software based on the three-dimensional model of the solid-liquid rocket.

The oxidant parameter window includes four data windows, oxidant quality, large flow, large flow working time, and small flow, which are input by the user through design requirements.

The gas cylinder pressure window is used to receive the actual gas cylinder initial pressure of the solid-liquid rocket entered by the user.

The full arrow length window is used to receive the initial full arrow length of the solid-liquid rocket input by the user.

The second input module 102 is also called solid-liquid engine fuel combustion data file input module, and is used for receiving the solid-liquid engine fuel combustion data file input by the user.

Specifically, the second input module includes an input file window and a browse button (or called an input file selection button) on the right side of the input file window. Users can click the browse button on the right side to search, and the designed solid-liquid engine can be burned The test data is imported into the program in the form of an Excel table. This module can import data from any location in the local computer, and display the path and file name in the input file window on the left side of the browse button for user inspection.

Further, the output module 300 includes a first output module 301 and a second output module 302 .

The first output module 301 is also called the calculation result file output module, which is used to write the mass centroid characteristic data into the automatically generated form according to the preset format to generate a data table file; save the generated data table file in a designated location .

Specifically, the operation result file output module will create an Excel table in the required format (preset format), and at the same time write the calculated data into the table according to the preset format, and finally obtain the required data table and save it in the input file under the same folder. The form of the data table is concise and can be used conveniently and directly. Automate the work of extracting data and improve the operating efficiency of computing personnel.

The second output module 302 is also called a graphic display module, which is used to generate a change curve according to the mass centroid characteristic data; and output the change curve to a display screen for display.

Specifically, the right side of the program main interface is provided with a graphic drawing and display area, and the graphic display module therein draws the solid-liquid rocket flight mass (expressed in m, unit kg) and the position of the center of mass ( Expressed in x, the unit is mm), the axial moment of inertia Ix and the vertical axis moment of inertia Iy are curves with flight time. It is convenient for the operator to conduct a preliminary intuitive analysis of the calculation results to judge the validity of the calculation results.

Further, the device also includes: a learning module 400 .

The learning module 400 is used to reasonably simplify the parts of the oxidant storage tank, the gas cylinder and the combustion chamber, and construct the calculation model of the oxidant storage tank, the gas cylinder and the combustion chamber.

Specifically, the learning module is used in the gas cylinder calculation part, assuming that the gas in the gas cylinder is a cylinder, and the outer diameter changes uniformly inward,

For the calculation part of the oxidant storage tank, it is assumed that the hydrogen peroxide in the storage tank is a cylinder, and the outer diameter changes uniformly inward, and the liquid bag model of the storage tank is simplified as a 2mm thick sleeve;

In the calculation part of the combustion chamber, it is assumed that the charge column of the solid-liquid engine is a single-hole cylinder, only the inner hole burns, and the charge surface retreats uniformly;

Based on the above basic assumptions, the corresponding oxidant storage tank calculation models, gas cylinder calculation models and combustion chamber calculation models are respectively established.

Further, the calculation module 200 is specifically used for:

Using the gas cylinder calculation model to calculate the first mass center of mass characteristic data of the gas cylinder system according to the initial pressure and mass of the gas cylinder in the parameter information;

Using the calculation model of the oxidant storage tank to calculate the second mass centroid characteristic data of the storage tank system according to the flow rate of the oxidant in the parameter information;

Use the combustion chamber calculation model to calculate according to the ground test data in the parameter information, and obtain the third mass centroid characteristic data of the combustion chamber system;

The first mass center characteristic data, the second mass characteristic data and the third mass characteristic data are calculated to generate the mass center of mass characteristic data of the solid-liquid rocket throughout the flight process.

Specifically, the calculation module includes a calculation button and a background calculation program, which are used to calculate the mass centroid characteristics of the full arrow, and its main body is the calculation of the mass characteristics of the solid-liquid engine system. Therefore, the calculation of the mass characteristics of the solid-liquid engine system is used here to characterize the mass center of mass characteristics of the solid-liquid rocket during the entire flight process; after the user clicks the calculation button, the device calculates the mass center of mass characteristics of the solid-liquid rocket during the flight according to the above input data. At the same time, the Excel table in the required format can be output through the output module, and the graphic display module can draw the change curve of mass, center of mass and moment of inertia with flight time.

Among them, the calculation method of the mass characteristics of the solid-liquid engine system is:

In the calculation part of the gas cylinder, it is assumed that the gas in the gas cylinder is a cylinder, and the outer diameter changes uniformly inward. Through the input of the initial pressure and mass of the gas cylinder, the remaining mass is calculated through proportional calculation during the flight, and the center of mass and the moment of inertia are calculated. Variety.

For the calculation part of the oxidant storage tank, it is assumed that the hydrogen peroxide in the storage tank is a cylinder, and the outer diameter changes uniformly inward, and the liquid bag model of the storage tank is simplified as a 2mm thick sleeve, combined with the calculation of the gas in the gas cylinder, the storage tank is calculated simultaneously The mass characteristics of the gas entering the tank, combined with the given oxidant flow rate, calculate the change of the overall mass, center of mass, and moment of inertia of the tank with the flight time.

For the calculation part of the combustion chamber, it is assumed that the charge column of the solid-liquid engine is a single-hole cylinder, only the inner hole burns, and the charge surface retreats uniformly. Through the input ground test data, the overall mass of the combustion chamber with the flight time can be calculated. The center of mass and moment of inertia change.

By rationally simplifying some models of storage tanks, gas cylinders, and combustion chambers, a corresponding calculation model is established, and data such as the mass, center of mass, and moment of inertia of each system are calculated separately, and finally the unified calculation is carried out to obtain the flight mass center of mass characteristics of the whole arrow (i.e. The center of mass characteristic data of the solid-liquid rocket during the whole flight process). Among them, the calculation of the center of mass can be calculated according to the analysis of the center of each part, and the calculation of the total moment of inertia is based on the moment of inertia of each part, using the parallel axis theorem to calculate.

Fig. 6 shows the schematic diagram of the interface of the automatic calculation device of the solid-liquid rocket flight mass characteristics provided by the embodiment of the present invention, the automatic calculation device of the solid-liquid rocket flight quality characteristics is based on rocket design theory and kinematic analysis, Establish a mathematical model, apply computer language for programming, and display a graphical user interface (GUI) to the user; the GUI includes a parameter input area, an output file area (including an output file window and a calculation button) and a graphics drawing area. The parameter input area includes various input windows. The parameter input area is set on the upper left side of the interface; the output file area is set on the lower left side of the interface; the graphics drawing area is set on the right side of the interface.

Below in conjunction with Fig. 7, the automatic calculation device for the flight quality characteristics of the solid-liquid rocket provided by the embodiment of the present invention is briefly described for the automatic calculation flow chart of the flight quality characteristics of the solid-liquid rocket:

1) start

Run the program to display the main interface of the program.

2) Enter parameter information

Input solid-liquid rocket parameters and solid-liquid engine fuel combustion data files.

3) calculate

Firstly, the combustor system, tank system and gas cylinder system are calculated, and the mass of fuel and oxidant in the combustor, the center of mass of the combustor and the moment of inertia of the coordinate system of the center of mass of the combustor, the mass of gas in the tank, the center of mass of the tank and the coordinates of the center of mass of the tank are respectively obtained The moment of inertia of the system, and the mass of gas in the gas cylinder, the center of mass of the gas cylinder and the moment of inertia of the coordinate system of the center of mass of the gas cylinder.

Then calculate the total mass and total moment of inertia.

4) output

Output the calculation result files of the above total mass and total moment of inertia, and at the same time, display the above total mass and total moment of inertia graphically.

5) end

The automatic calculation device for the flight quality characteristics of the solid-liquid rocket provided by the embodiment of the present invention has the following advantages:

1. The automatic calculation device for the flight mass characteristics of solid-liquid rockets according to the present invention can enable staff in any industry to clearly know the information content that should be filled in each window in the information input module after entering the main interface of the program, so as to avoid In addition, it needs to be filled in according to the name and sequence list provided by the developer. If the paper name list is lost, it cannot be used, which greatly improves the practicability and convenience; one kind of information corresponds to one window, and the windows are arranged in order from top to bottom , making the program more orderly and clear.

2. In the calculation part of the solid-liquid engine, the parameters of the solid-liquid engine components such as tanks, gas cylinders, and combustion chambers can be easily calculated by rationally simplifying the model. By combining with the ground test parameters, the high-accuracy flight quality characteristics can be calculated.

3. Through program encapsulation, you only need to input the data required for calculation in a fixed format, and then you can perform calculations correctly and obtain the required results. The entire operation process is greatly simplified.

4. Automate the data sorting and writing process, and directly obtain the Excel table of the data in the required format after calculation, improving the efficiency of operators.

5. Set the graphics display area, and draw the calculation results in the relevant area of the panel to draw curves after the calculation, which is convenient for visual analysis of the results, judging the validity of the calculation results, and further improving the calculation efficiency.

6. The distribution of each functional area is clear, the interface of the entire calculation program is clear and concise, the program is easy to install on different computers, and the operation is simple and easy to use.

Embodiment three:

8, the embodiment of the present invention also provides an electronic device 800, including: a processor 40, a memory 41, a bus 42 and a communication interface 43, the processor 40, the communication interface 43 and the memory 41 are connected through the bus 42; processing The processor 40 is used to execute executable modules stored in the memory 41, such as computer programs.

Wherein, the memory 41 may include a high-speed random access memory (RAM, RandomAccessMemory), and may also include a non-volatile memory (non-volatile memory), such as at least one disk memory. The communication connection between the system network element and at least one other network element is realized through at least one communication interface 43 (which may be wired or wireless), and the Internet, wide area network, local network, metropolitan area network, etc. can be used.

The bus 42 can be an ISA bus, a PCI bus or an EISA bus, etc. The bus can be divided into address bus, data bus, control bus and so on. For ease of representation, only one double-headed arrow is used in FIG. 8 , but it does not mean that there is only one bus or one type of bus.

Wherein, the memory 41 is used to store the program, and the processor 40 executes the program after receiving the execution instruction, and the method performed by the flow process definition device disclosed in any of the embodiments of the present invention described above can be applied to processing In the device 40, or implemented by the processor 40.

The processor 40 may be an integrated circuit chip with signal processing capabilities. In the implementation process, each step of the above method can be completed by an integrated logic circuit of hardware in the processor 40 or instructions in the form of software. The above-mentioned processor 40 can be a general-purpose processor, including a central processing unit (Central Processing Unit, referred to as CPU), a network processor (Network Processor, referred to as NP), etc.; it can also be a digital signal processor (Digital Signal Processing, referred to as DSP) , Application Specific Integrated Circuit (ASIC for short), off-the-shelf programmable gate array (Field-Programmable Gate Array, FPGA for short) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components. Various methods, steps and logic block diagrams disclosed in the embodiments of the present invention may be implemented or executed. A general-purpose processor may be a microprocessor, or the processor may be any conventional processor, or the like. The steps of the methods disclosed in connection with the embodiments of the present invention may be directly implemented by a hardware decoding processor, or implemented by a combination of hardware and software modules in the decoding processor. The software module can be located in a mature storage medium in the field such as random access memory, flash memory, read-only memory, programmable read-only memory or electrically erasable programmable memory, register. The storage medium is located in the memory 41, and the processor 40 reads the information in the memory 41, and completes the steps of the above method in combination with its hardware.

The automatic calculation device and electronic equipment for the flight quality characteristics of solid-liquid rockets provided by the embodiments of the present invention have the same technical characteristics as the automatic calculation methods for the flight quality characteristics of solid-liquid rockets provided by the above-mentioned embodiments, so the same technical problems can also be solved , to achieve the same technical effect.

The computer program product of the automatic calculation method for the flight mass characteristics of the solid-liquid rocket provided by the embodiment of the present invention includes a computer-readable storage medium storing non-volatile program code executable by the processor, and the program code includes The instructions can be used to execute the methods described in the foregoing method embodiments. For specific implementation, please refer to the method embodiments, which will not be repeated here.

Those skilled in the art can clearly understand that for the convenience and brevity of the description, the specific working process of the above-described device and electronic equipment can refer to the corresponding process in the foregoing method embodiment, which will not be repeated here.

The flowchart and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of methods and computer program products according to various embodiments of the present invention. In this regard, each block in a flowchart or block diagram may represent a module, program segment, or part of code that includes one or more Executable instructions. It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks in succession may, in fact, be executed substantially concurrently, or they may sometimes be executed in the reverse order, depending upon the functionality involved. It should also be noted that each block of the block diagrams and/or flowchart illustrations, and combinations of blocks in the block diagrams and/or flowchart illustrations, can be implemented by a dedicated hardware-based system that performs the specified function or action , or may be implemented by a combination of dedicated hardware and computer instructions.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, or in a specific orientation. construction and operation, therefore, should not be construed as limiting the invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and should not be construed as indicating or implying relative importance.

In the several embodiments provided in this application, it should be understood that the disclosed systems, devices and methods may be implemented in other ways. The device embodiments described above are only illustrative. For example, the division of the units is only a logical function division. In actual implementation, there may be other division methods. For example, multiple units or components can be combined or May be integrated into another system, or some features may be ignored, or not implemented. In another point, the mutual coupling or direct coupling or communication connection shown or discussed may be through some communication interfaces, and the indirect coupling or communication connection of devices or units may be in electrical, mechanical or other forms.

The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place, or may be distributed to multiple network units. Part or all of the units can be selected according to actual needs to achieve the purpose of the solution of this embodiment.

In addition, each functional unit in each embodiment of the present invention may be integrated into one processing unit, each unit may exist separately physically, or two or more units may be integrated into one unit.

If the functions are realized in the form of software function units and sold or used as independent products, they can be stored in a non-volatile computer-readable storage medium executable by a processor. Based on this understanding, the essence of the technical solution of the present invention or the part that contributes to the prior art or the part of the technical solution can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including Several instructions are used to make a computer device (which may be a personal computer, a server, or a network device, etc.) execute all or part of the steps of the methods described in various embodiments of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), magnetic disk or optical disk and other media that can store program codes. .

Finally, it should be noted that: the above-described embodiments are only specific implementations of the present invention, used to illustrate the technical solutions of the present invention, rather than limiting them, and the scope of protection of the present invention is not limited thereto, although referring to the foregoing The embodiment has described the present invention in detail, and those skilled in the art should understand that any person familiar with the technical field can still modify the technical solutions described in the foregoing embodiments within the technical scope disclosed in the present invention Changes can be easily thought of, or equivalent replacements are made to some of the technical features; and these modifications, changes or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be included in the scope of the present invention within the scope of protection. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims (10)

1. a kind of automation computational methods of solid-liquid rocket flight reappearance characteristic, which is characterized in that including：

Receive parameter information input by user；Wherein, the parameter information include solid-liquid engine fuel burning data file and Rocket structure parameter；

The quality center of mass performance data of the entire flight course of solid-liquid rocket is generated according to the parameter information；

The quality center of mass performance data is exported.

2. according to the method described in claim 1, it is characterized in that, described export the quality center of mass performance data, It specifically includes：

The quality center of mass performance data is written according to preset format in the table automatically generated, generates data list file；

The data list file of generation is stored in designated position；

And/or

According to the quality center of mass performance data, change curve is generated；

The change curve is exported to display interface.

It is 3. according to the method described in claim 1, it is characterized in that, described entire according to parameter information generation solid-liquid rocket The quality center of mass performance data of flight course, specifically includes：

The first of gas cylinder system is obtained using the initial pressure of gas cylinder of the gas cylinder computation model in parameter information and Mass Calculation Quality center of mass performance data；

The second matter of tank system is calculated using oxidizer flow rate of the oxidant tank computation model in parameter information Measure barycenter performance data；

It is calculated using ground test data of the combustion chamber computation model in parameter information, obtains the of chamber system Three quality center of mass performance datas；

Above-mentioned first quality center of mass performance data, the second quality characteristics data and third quality characteristics data are calculated, it is raw Into the quality center of mass performance data of the entire flight course of solid-liquid rocket.

4. it according to the method described in claim 3, it is characterized in that, further includes：

Respectively to oxidant tank, gas cylinder and combustor section carry out Rational Simplification, structure obtain oxidant tank computation model, Gas cylinder computation model and combustion chamber computation model.

It is 5. according to the method described in claim 4, it is characterized in that, described respectively to oxidant tank, gas cylinder and combustor section Divide and carry out Rational Simplification, structure obtains oxidant tank computation model, gas cylinder computation model and combustion chamber computation model, specific to wrap It includes：

Process to simplify the calculation makees following basic assumption：

Gas cylinder calculating section, it is assumed that gas is cylinder in gas cylinder, even variation in outer radial；

Oxidant tank calculating section, it is assumed that tank hydrogen peroxide is cylinder, even variation in outer radial, and simplifies tank Liquid capsule model is 2mm thickness sleeves；

Combustion chamber calculating section, it is assumed that the powder column of solid-liquid engine is single-hole cylindrical body, and only internal bore burning, powder is uniformly retired；

Based on above-mentioned basic assumption, corresponding oxidant tank computation model, gas cylinder computation model and combustion chamber meter are established respectively Calculate model.

6. a kind of automation computing device of solid-liquid rocket flight reappearance characteristic, which is characterized in that including：

MIM message input module, for receiving parameter information input by user；Wherein, the parameter information is fired including solid-liquid engine Expect burning data file and rocket structure parameter；

Computing module, for generating the quality center of mass performance data of the entire flight course of solid-liquid rocket according to the parameter information；

Output module, for the quality center of mass performance data to be exported.

7. device according to claim 6, which is characterized in that described information input module includes the first input module and the Two input modules；

First input module is used to receive rocket structure parameter input by user；Wherein, first input module includes structure Mass window, structure barycenter window, rotary inertia Ix windows, rotary inertia Iy windows, oxidant parameter window, storage pressure window Mouth, whole rocket length window；

Second input module is used to receive solid-liquid engine fuel burning data file input by user.

8. device according to claim 6, which is characterized in that the output module is defeated including the first output module and second Go out module；

First output module is used for the table for automatically generating the quality center of mass performance data according to preset format write-in In, generate data list file；The data list file of generation is stored in designated position；

Second output module is used to, according to the quality center of mass performance data, generate change curve；By the change curve It exports to display interface.

9. device according to claim 6, which is characterized in that further include：

Study module, for carrying out Rational Simplification to oxidant tank, gas cylinder and combustor section respectively, structure obtains oxidant Tank computation model, gas cylinder computation model and combustion chamber computation model.

10. device according to claim 9, which is characterized in that the computing module is specifically used for：

The first of gas cylinder system is obtained using the initial pressure of gas cylinder of the gas cylinder computation model in parameter information and Mass Calculation Quality center of mass performance data；

The second matter of tank system is calculated using oxidizer flow rate of the oxidant tank computation model in parameter information Measure barycenter performance data；

It is calculated using ground test data of the combustion chamber computation model in parameter information, obtains the of chamber system Three quality center of mass performance datas；

Above-mentioned first quality center of mass performance data, the second quality characteristics data and third quality characteristics data are calculated, it is raw Into the quality center of mass performance data of the entire flight course of solid-liquid rocket.