CN117113645A - Rapid generation system for large-scale space training task scene - Google Patents

Abstract

The invention relates to the field of trial training task scene generation, in particular to a large-scale space trial training task scene rapid generation system. The system of the invention comprises: the system comprises: the system comprises a task training environment generation module, a spacecraft generation module, a task orbit generation module and a training task scene generation module; the task training environment generation module is used for generating a task training environment through space environment data or a calculation mode; the spacecraft generation module is used for constructing shelf type elements and generating different spacecraft based on the combination of the shelf type elements in a man-machine interaction mode; the task track generation module is used for generating a task track in a graphical interactive mode; and the training task scene generation module is used for fusing the task training environment, the spacecraft and the task orbit to form a training task scene. The invention realizes the real and flexible construction of the training task scene in a large-scale space and provides technical support for training and tactical research in training simulation.

Description

Rapid generation system for large-scale space training task scene

Technical Field

The invention relates to the field of trial training task scene generation, in particular to a large-scale space trial training task scene rapid generation system.

Background

At present, military training faces the practical training problems of novel and unique combat mode, dynamic change of combat objects, complex combat conditions and the like, and the most practical military operation under peace environment is training practice, if combat test is carried out in combination with training practice, the requirement of actual combat can be met, the training cost is greatly reduced, the training safety is ensured, and meanwhile, the practical system is not interfered.

With the sustainable development of informatization construction in the field of test training, military training advances deeply to actual combat, and is reflected in expansion of test objects to equipment systems, transformation of test environments to complex environments, integrated joint transformation of test modes and the like. A training system closely attached to actual combat is constructed through simulation, and the training system supports troops to develop activities such as post operation training and systematic countermeasure training, so that training scenes can be flexibly laid, training contents are enriched, and training effects can be effectively improved.

The task scene construction of the training system not only accords with the characteristics of various space training means, complex system, various elements and the like, but also needs to construct different training scene contents by flexibly setting training scene parameters so as to meet the requirements of post operation training, tactical study and the like. In the training scene construction process, besides the rapid construction of the spacecraft structure and the task orbit design, the space environment which has important influence on the orbit design and control, equipment safety, task planning and the like of the spacecraft is more important at any time. Space environments such as magnetic fields, radiation bands, solar winds, and the like can have different degrees of influence and damage on spacecraft communications, energy, structures, electronic devices, load performance, and the like.

At present, the training system rarely considers the introduction and influence of factors such as space environment, even if the factors are involved, certain environmental factors are introduced from the front end display perspective, and the requirement of closely attaching to actual environment simulation is far less. Meanwhile, the task scenes such as task tracks and spacecraft structures are built in a parameterized mode through template matching or user input mode, and the mode is not intuitive and simple and cannot meet the requirement of rapid building.

In summary, in the training system facing to the complex environment and system countermeasure, the rapid construction of the large-scale, flexible and real training task scene is a foundation and core for developing the training task, and is a great challenge.

Disclosure of Invention

The invention aims to solve the problem that the large-scale real training task scene is difficult to generate rapidly in the field of space training. The invention breaks through key technologies of rapid construction of environmental elements, rapid design of shelf type spacecraft structure, rapid design of task orbit based on characteristics and the like facing to trial training tasks, realizes real and flexible construction of trial training task scenes in large-scale space, and provides technical support for training and tactical research under training simulation.

The main purposes of the invention specifically comprise:

1. the flexibility of spacecraft structure and orbit design is greatly enhanced, the degree of freedom of weapon force layout in training scenes is further expanded, and scene construction and training efficiency are effectively improved.

2. The development of a training system integrating the influence of the space environment is promoted, so that the training system develops towards a direction which is more closely attached to the actual situation.

In order to achieve the above purpose, the present invention is realized by the following technical scheme.

The invention provides a large-scale space training task scene rapid generation system, which comprises:

the task training environment generation module is used for generating a task training environment through space environment data or a calculation mode;

the spacecraft generation module is used for constructing shelf type elements and generating different spacecraft based on the combination of the shelf type elements in a man-machine interaction mode;

the task track generation module is used for generating a task track in a graphical interactive mode; and

and the training task scene generation module is used for fusing the task training environment, the spacecraft and the task orbit to form a training task scene.

As one of the improvements of the above technical solution, in the task training environment generating module, generating a task training environment includes: generating an earth magnetic field, generating an earth radiation band and generating solar wind; wherein the earth's magnetic field comprises an endogenous field and an exogenous field;

The generating an earth magnetic field includes: calculating an intrinsic field by adopting an international standard 'international reference geomagnetic field' in geophysics, and calculating an extrinsic field by adopting a T96 magnetic layer magnetic field mode; and the magnetic force lines are adopted to characterize the earth magnetic field;

the generating an earth radiation band comprising: calculating an earth radiation band by adopting an electron AE8 mode and a proton AP8 mode, and carrying out the calculation by adopting a mode of fusing an outermost layer, and representing the earth radiation band by carrying out visual representation on the distribution condition of omnidirectional integral fluxes of protons and electrons with different energies in the radiation band in space;

the generating solar wind includes: simulating the density, temperature, speed and magnetic field distribution of the solar wind plasma in space according to the existing observation data within the space range of 1AU, wherein the density and the temperature are described by only one data item; the speed and the magnetic field strength are required to be determined by components in the directions of 3 coordinate axes; the method is characterized in that the density or the temperature is represented by converting a data item into a color based on a color table, and the representing effect of speed and magnetic field intensity is generated by interpolation in solar wind data by adopting a magnetic line generation mode in a method for rapidly generating the earth magnetic field.

As one of the improvements of the above technical solution, the calculation formulas of the north component X, the east component Y and the vertically downward component Z of the endogenous field are respectively:

wherein, (r, θ, λ) is the geocentric coordinates, r is the geocentric distance, θ is the geographic residual latitude; λ is the geographic longitude, a is the earth radius,and->Is a Gaussian coefficient of a certain order N at time t, < >>Is an n-order m-order Schmidt quasi-normalized Legendre function;

the T96 magnetic layer magnetic field mode is to calculate an external magnetic field at a certain point in space by using solar wind pressure, DST index, inter-planetary magnetic field and geomagnetic inclination angle;

the magnetic field of the earth is characterized by magnetic lines of force, and the method specifically comprises the following steps: determining an initial position point P1 of magnetic force lines, advancing to P2 in the magnetic field direction by a small step length T according to the magnetic field intensity of the point, and repeating the process at the point P2 until reaching the boundary of a data field or other termination conditions; the magnetic field intensity of any point P is calculated by adopting an international reference geomagnetic field or T96 magnetic layer magnetic field mode according to the position of the magnetic field intensity;

when simulating the distribution condition of the density, the temperature, the speed and the magnetic field of the plasmas of the solar wind in space, sampling the data of the solar wind in space in the polar coordinate space, and specifically comprises the following steps:

The reference coordinate axis of the solar yellow track coordinate system is marked by an x axis, a y axis and a z axis, and the reference coordinate axis is marked byDetermining the spatial position of each sampling point in a ternary manner, wherein r 'is the distance from the sampling point to the sun center, θ' is the included angle between the projection of the sampling point and the center line in the yellow road surface and the x-axis of the coordinate system of the sun center yellow road, and->Is the included angle between the connecting line of the sampling point and the sun center and the z axis of the coordinate system of the yellow track of the sun center; the attribute field for each sample point includes: background field density, background field temperature, particle density at a certain simulation time, temperature, magnetic field strength and radial velocity; the closer to the centroid the data sampling frequency per unit distance is, the higher the sampling.

As one of the improvements of the above technical solutions, in the spacecraft generation module, constructing the shelf element includes: summarizing and summarizing three-dimensional characteristics of each spacecraft platform and load, extracting a three-dimensional structure of a typical part for digitizing, defining a geometric model, establishing a model template and a module, and providing a corresponding construction method and a module library; wherein,

defining geometric topological features, shape features, working features, material features and quality features of the geometric model; when defining the working characteristics, at least performing coverage analysis, shielding analysis and communication analysis on the components; at least the rendering analysis, the mechanical analysis, and the thermal analysis are performed on the part when defining the operational characteristics.

As one of the improvements of the above technical solution, in the spacecraft generating module, when different spacecraft are generated based on the combination of shelf type elements in a man-machine interaction manner, a structural design mode from bottom to top is adopted to perform three-dimensional design of components, and then the components are assembled step by step to complete assembly of the whole spacecraft structure, which specifically comprises:

a) Establishing a blank design scene;

b) Selecting the type of a spacecraft platform, and adjusting the size of each part of the spacecraft platform;

c) Selecting an internal load component of the spacecraft, and adjusting parameters including size and weight;

d) The method comprises the steps of installing and detecting the internal load of a platform, including collision and adsorption, setting the installation posture of the load at the same time, and determining the size and the direction of a load visual field;

e) The external load of the mounting platform is adjusted, characteristic parameters including size, weight and material are adjusted, the size and the direction of a detection view field are set, the type of a turntable is selected, and a movement mode is installed and set;

f) Selecting a communication antenna type, an installation mode and an installation position;

g) Selecting a solar sailboard type, and setting an installation position and an unfolding mode;

h) And (5) completing the structural design of the spacecraft.

As one of the improvements of the above technical solution, the task track generation module includes: a space generating unit, a celestial body generating unit, a track calculating and adjusting unit, wherein,

The space generating unit is used for establishing a three-dimensional virtual space and a reference coordinate system;

the celestial body generating unit is used for establishing celestial bodies in the solar system in the three-dimensional virtual space, including the position, the speed and the rotation of the celestial bodies, and dividing the celestial bodies into longitude and latitude;

the track calculation and adjustment unit is used for establishing, adjusting and generating a task track in the three-dimensional virtual space through the track feature points.

As one of the improvements of the above technical solution, in the track calculation and adjustment unit, a task track is established, adjusted and generated in a three-dimensional virtual space through track feature points, including:

establishing a default track as an operation object in a mode of directly drawing on a screen, clicking or inputting parameters from a system background database, wherein when the default track is directly drawn and established on the screen, the relative relation between the track characteristic points, a central celestial body and a virtual three-dimensional space is utilized to extract input information required by track root number calculation, and the calculation of the quick track root number is completed;

after the default track is established, the shape and the azimuth of the track are changed by adjusting a series of track characteristic points reflecting the current track measurement information on the track until the track can cover the adjustment of the track of the task target which is required to be completed by the user, and a task track is generated.

As one of the improvements of the above technical solution, in the process of completing the calculation of the fast track number, when the track is an elliptical track, the calculated track number includes: the semi-long axis a, the eccentricity e, the track inclination angle i, the near-place radial angle omega, the rising intersection point right ascent angle omega and the true near-point angle f are calculated as follows:

wherein r is _a ,r _p The far and near spot radii of the target track are respectively represented: r is (r) _a ＝d _B ,r _p ＝d _A ；d _j Representing the distance from the reference point j to the center point; (x) _j ，y _j ，z _j ) Representing the coordinate P of the reference point j _j ；

Wherein H represents the modulus of the track normal vector H;

H＝(h _x h _y h _z ) ^T ＝P _A ×P _C ＝P _C ×P _B ＝P _B ×P _D ＝P _D ×P _A ，(h _x h _y h _z ) Representing a track normal vector;

wherein O is the center of coordinates, P _a (x _a ,y _a ,z _a =0) is the intersection of the rises, ||op _a The I represents the mode of the vector of the line connecting the ascending intersection point and the coordinate center; the method comprises the steps of carrying out a first treatment on the surface of the

In the method, in the process of the invention, the terms represent the modulus of the vector;

the true near point angle f is determined by the position in orbit of the user dragging the satellite.

As one of the improvements of the above technical solution, in the track calculation and adjustment unit, a task track is established, adjusted and generated in a three-dimensional virtual space by using track feature points, and the method further includes: after the rapid track number calculation is completed, the track number is converted into track parameters under a Cartesian coordinate system, and then the track parameters under the Cartesian coordinate system are used for recursive calculation, so that a more accurate track is obtained.

As an improvement of the foregoing solution, the converting the number of tracks to the track parameters in the cartesian coordinate system includes:

f) Calculating a current ground center distance r:

g) Calculating the amplitude angle u of the current satellite:

u＝ω+f

h) Three components x, y, z of the current satellite position are calculated:

wherein, the s point is the projection of the satellite on the celestial sphere, r is the earth center distance, i is the orbit inclination angle, u is the amplitude angle of the current satellite, and Ω is the right ascent intersection point;

i) Calculating the current satellite rate v:

wherein μ is the gravitational constant;

j) Calculating the component of velocity

Wherein,s' represents the pointing point of the satellite velocity direction in the orbital plane, and m represents one derivation; the angle between s' and s satisfies:

f at the I, II quadrant number,in quadrant I; f in quadrant III, IV, < >>In quadrant II.

When the track parameters under Cartesian coordinates are used for recursive calculation, a recursive formula is as follows:

wherein x, y and z are satellite coordinates, and represent secondary derivation;is the distance from the satellite to the earth center.

Compared with the prior art, the invention has the advantages that:

1. the system realizes the rapid generation of the space environment typical elements facing the training task; aiming at the problem of space environment influence on a spacecraft in a training task, a typical element rapid generation method for reflecting the distribution rule, data connotation and change characteristics of environmental elements is provided, the value of the whole space environment is rapidly calculated through an environmental element mode, the requirement that the training task is used for taking the value of the whole space in the whole time without being consistent with the objective world at any time is met, the requirement of tight fitting actual combat is basically met, and the method has high application value;

2. The system of the invention realizes the rapid generation of the force structure and the track under the training scene; aiming at the problems that space trial training tasks are complex, scene creation and change are frequent, and group training staff often do not have a structure or are special for a rail, and special tools are difficult to use, the method for quickly generating the structure and the rail of the spacecraft is provided, the conventional design mode in the field of space trial training is subverted through shelf type assembly or drag type characteristic rail modification, the method is an application research work with a certain original innovation, and the use efficiency of the personnel in the field is greatly improved.

Drawings

FIG. 1 is a diagram of three key technical roadways involved in a large-scale space training task scenario rapid generation system, mainly illustrated;

FIG. 2 is a schematic view of the spatial location of a solar wind sampling point;

fig. 3 (a) -3 (c) are schematic views of several operational features, where fig. 3 (a) is a linear scan field schematic, fig. 3 (b) is a pyramid field schematic, and fig. 3 (c) is a cone field schematic;

FIG. 4 is a schematic diagram of a shelf type element organization;

FIG. 5 is a component-based spacecraft assembly method interface schematic;

FIG. 6 is a schematic view of a platform assembly;

FIG. 7 is a feature point based track quick build graph;

FIG. 8 is a spherical relationship of satellites;

FIG. 9 is a graph of a daylight background generation effect;

FIG. 10 is a view showing the effect of solar celestial body generation;

FIG. 11 is an earth multi-resolution generation effect graph;

FIG. 12 is a graph of the effects of earth's magnetic field generation;

FIG. 13 is a cross-sectional visualization effect map based on radiation band data;

FIG. 14 is a diagram of the solar-wind interplanetary effect;

FIG. 15 is a diagram of the effects of a shelf spacecraft architecture rapid design;

FIG. 16 is a diagram of a feature-based task track rapid design effect.

Detailed Description

The technical scheme of the invention is described in detail below with reference to the accompanying drawings and examples.

The invention relates to a training task scene generation system, in particular to a rapid generation system for scenes such as space environment, spacecraft and the like under a large-scale space countermeasure training task in the field of space training.

The patent designs a rapid generation system for space environment, spacecraft and other scenes under a large-scale space countermeasure training task, and the technical route is shown in figure 1. Aiming at the rapid generation requirement of a large-scale space training task scene, a task training environment is firstly generated through space environment data or a calculation mode, different spacecrafts are generated based on pre-built goods shelf products in a man-machine interaction mode, a drag type mode for adjusting track characteristic points is adopted to see, namely, the effect of environmental factors is considered to generate a task track, and finally the training task scene is formed through environment and spacecraft data fusion. Of course, constructing the space task scene without separating celestial body surface, namely, simulating and constructing the celestial light background, solar system celestial body and celestial body surface environment, wherein the celestial light background construction can realize the generation and drawing of constellations, stars, star clouds and the like based on the data of the public star meters such as the ibagu star meter, the SAO meter and the like; the solar system celestial body simulation can drive solar system planets and satellites to move according to real ephemeris data to form a solar system celestial body movement scene; the celestial body surface environment is constructed as a surface environment, the topography and the relief of the celestial body surface environment are realized by adopting a texture mapping mode based on multi-resolution geographic data, and the atmospheric effect is generated and rendered based on a single scattering model. The patent mainly describes three key technologies based on the basic scenes: an environment element rapid construction technology for trial training tasks, a shelf type spacecraft structure rapid design technology and a task orbit rapid design technology based on characteristics.

1. Quick construction technology of environment elements for training task

With the high-speed development of aerospace application in China, environmental information such as magnetic fields, radiation fields and the like in the space of the spacecraft, namely the near/deep space, is increasingly important to the running and safety of space tasks. The space environment data relates to various physical fields such as magnetic fields, gravitational fields, solar wind and the like in a near-earth space, a daily-earth space and even an inter-satellite space, the data types comprise various types such as two-dimensional/three-dimensional scalar, vector fields, images and the like, a reference coordinate system is complex and highly dynamic, and the space distribution, the motion rule and the dynamic characteristics of the space environment can be intuitively displayed in front of people and are directly perceived by human vision through rapid construction and expression of the large-scale multidimensional space environment information; on the other hand, the three-dimensional space of the space environment is displayed through the three-dimensional visual image, and the auxiliary support can be provided for the simulation, training and research of the space task by combining the space task demand analysis.

The space environment has the characteristics of large space-time scale span, complex reference coordinate system, large environment data volume, high dynamic change, difficult expression of non-visual information and the like, and the real-time high-precision simulation of the space environment is not realistic at present. Meanwhile, in the trial training task simulation, a space environment completely consistent with the objective world is not necessarily needed, and more importantly, the distribution rule, the data connotation and the change characteristics of each type of environment elements are reflected, so that the understanding of training personnel on the space environment knowledge, the perception of factors and the application of the effects can be promoted, and the space environment cognition level and the training effect are improved. The method of rapid generation will be described herein by taking the construction of a typical spatial environment such as the earth's magnetic field, radiation band, solar wind, etc.

(1) Method for quickly generating earth magnetic field

The geomagnetic field is formed by superposition of various magnetic field components generated by magnetic rocks in the earth and a current system distributed in the earth and outside, and can be divided into an endogenous field and an exogenous field according to the origins of the magnetic fields. The geomagnetic field is a vector field that is a function of spatial position and time.

In the rapid generation of the geomagnetic field, the endogenous field is calculated using the international standard "international reference geomagnetic field" (IGRF) in geophysics. It is expressed in the form of a number of spherical harmonics, the highest order of which is typically 10, for a total of 120 spherical harmonic coefficients. In the passive region of near earth space, the main magnetic field originating inside the earth can be represented as a negative gradient of magnetic potential V, while V can be spread out in the form of spherical harmonics:

where γ, θ, λ are geocentric coordinates (γ is the geocentric distance; θ is the geographic latitude, i.e., 90-geographic latitude; λ is the geographic longitude), α is the earth radius,and->Is the Gaussian coefficient at time t, +.>Is an n-order m-th order Schmidt quasi-normalized Legendre function. The international reference geomagnetic field assumes that the change of the main magnetic field is linear within 5 years, and the prediction coefficient is changedAnd->Giving the change in main magnetic field over the next 5 years.

The relationship between the magnetic field and the magnetic potential is:

Thus, the north component X, east component Y and vertically downward component Z of the geomagnetic field are respectively

Three components of the basic magnetic field at any point can be obtained from the above expression as long as the gaussian coefficient is given. Fitting the obtained Gaussian coefficient with a certain order N according to a large number of detection resultsAnd->The three components of the magnetic field can be found by the following formula:

the spatial distribution of the magnetic field above the ground and within 6 earth radii (Re) can be completely determined using the above expression and the coefficients of the corresponding times.

Since the magnetic field generated by the magnetic layer current system cannot be ignored in the space except for 6Re, the geomagnetic field of the external source field is rapidly generated and calculated by adopting the T96 magnetic layer magnetic field mode which is widely used in the research of many space physical problems at present. The T96 magnetic layer magnetic field pattern is an empirical pattern obtained by analytical fitting based on 36682 magnetic field vector observations taken by a plurality of satellites at different magnetic disturbance levels, which observations cover a considerable magnetic layer space. The magnetic field pattern is suitable for a spatial range of 4-70 earth radii. The magnetic field generated By the main magnetic field and the main magnetic layer current system is used for calculating an external magnetic field B= (Bx, by, bz) model of a space point (X, Y, Z) By using solar wind pressure, DST index, inter-planet magnetic field and geomagnetic inclination angle. Bx is called the north component of the geomagnetic field, by the east component of the geomagnetic field, bz becomes the vertical component of the geomagnetic field.

The magnetic field is typically characterized by magnetic field lines. The magnetic force line is a virtual curve, the magnetic force line is tangential to the magnetic induction intensity everywhere, the direction of the magnetic induction intensity is consistent with the direction of the magnetic force line, and the size of the magnetic force line is in direct proportion to the density of the magnetic force line. For this three-dimensional vector field of magnetic fields, P is one of the points, which is located at r. The magnetic force line passing through P is a space curve, r is a function of t, and has

Solving the equation can construct a field line for an instant.

Let the field lines be r (t) ≡x (t), y (t), z (t)] ^T Is a solution of the equation, the integral expression of the field line in the physical space is:

the above equation shows that the field lines are generated in small steps t starting from an initial position, r (0) being the initial condition. The basic principle for generating geomagnetic magnetic lines is as follows: the initial position P1 of the magnetic field lines is determined, and the process is repeated at point P2 until the boundary of the data field or other termination condition is reached, by advancing to point P2 in the direction of its magnetic field by a small step t, depending on the magnetic field strength of the point. The magnetic field intensity of any point P is calculated by adopting an international reference geomagnetic field or T96 magnetic layer magnetic field mode according to the position of the point P.

(2) Method for quickly generating earth radiation band

The earth radiation band includes an inner radiation band centered at about 1.5Re and having a magnetic pick of + -40 deg. and an outer radiation band 3-4Re, about 6000 km thick, which may extend to a spatial extent of 50 deg. to 60 deg. from the magnetic pick. These areas are filled with high energy charged particles and observed statistics show that magnetic storms, strong sub-storms, tend to cause severe failures in satellites operating in the radiation belt areas.

The radiation band particles are mainly subjected to the strong action of the geomagnetic field, under which the charged particles in the radiation band are periodically moved over a number of drum-shaped surfaces called "shells". The L-B coordinate system is often used to describe the spatial distribution of radiation band particles. B is the magnetic field intensity of a certain specific point in space, and takes Gauss as a unit; l is a magnetic shell parameter, and L is a constant for a particular magnetic shell. Under the approximation of the geomagnetic field of the center dipole, L is the distance of the magnetic shell on the equatorial plane, and takes the earth radius Re as a measurement unit.

The radiation band is rapidly generated by adopting the radiation band mode developed by internationally popular NASA, namely an electronic AE8 mode and a proton AP8 mode. This model is an average and static empirical model compiled from satellite data, giving particle fluxes of electrons and protons in different energy ranges (0.1-400 Mev) within the spatial range (1.15-6.6L), the spatial position of each particle being determined by the B-L coordinates.

The radiation band is characterized by adopting an outermost fusion section mode, and the distribution condition of the omnidirectional integral flux of protons and electrons with different energies in the radiation band in space is visually represented. Specifically, two different longitudinal sections and the outermost layer between the two sections are rendered, the proton or electron flux of the point on the surface where the color and transparency are represented by colors, each value corresponds to one color, and the change in flux size is represented by the change in color.

(3) Rapid generation method of solar wind

The solar wind fills the entire interplanetary space of the solar dome system and is formed and emitted from the corona at the outermost layer of the solar atmosphere. The corona has a large-scale dark area, which is an open area of a solar magnetic field, and the magnetic line of the area diffuses toward the universe space, and a large amount of plasmas run out along magnetic lines to form a high-speed moving particle stream, and when the particle stream reaches the vicinity of an earth orbit, the speed can reach more than 300-400 km per second. This high velocity moving plasma stream is known as solar wind. At present, a unified reference model does not exist for the change rule of solar wind, so that the solar wind rapid generation method simulates the distribution condition of the density, temperature, speed and magnetic field of the plasma of the solar wind in space according to the existing observation data within a space range of 1AU (distance between the sun and the earth). Wherein density and temperature are scalar fields, the property can be described by only one data item; while the velocity and the magnetic field strength are vector fields, the properties need to be determined by components in the direction of 3 coordinate axes.

The spatial domain of solar wind data is a sphere, and spatial data needs to be sampled in polar coordinate space. As shown in fig. 2: the x-axis, the y-axis and the z-axis are marked as reference coordinate axes of a solar yellow road coordinate system, P is a certain sampling point in space, r is the distance from the sampling point P to the sun center, θ is the included angle between the projection of the sampling point P and the center line in the yellow road surface and the x-axis of the sun yellow road coordinate system, Is the included angle between the connecting line of the sampling point and the sun center and the z-axis of the coordinate system of the yellow track of the sun center, which is formed by +.>The ternary equation determines the spatial position of each sampling point P. The attribute field for each sample point includes: background field density, background field temperature, and particle density, temperature, magnetic field strength, and radial velocity at some simulation time. In the spatial range with 1Au as radius and sun as center, at each simulation time, the spatial resolution of the data is: 154*55*80. Sampling data in view of the fact that the rate of change of the property values of the sampling points decreases with increasing distance from the center of dayThe non-uniform sampling method is taken-the closer to the centroid, the higher the data sampling frequency per unit distance. In terms of time resolution, the simulation data record the change of solar wind attribute data with time in 50 continuous hours, namely 100 simulation time points, at intervals of 0.5 hour. At the propagation speed of the solar wind, 50 hours is sufficient to allow the energetic particles ejected from the solar crown to propagate from the sun to the earth.

The solar wind data are characterized in that the density and the temperature are scalar fields, and the solar wind data can be described by converting the solar wind data into colors based on a color table through one data item; the speed and the magnetic field intensity are vector fields, which are required to be determined by components in the directions of 3 coordinate axes, and the representation effect of the solar wind vector field can be generated by interpolation in solar wind data by adopting a magnetic line generation mode in a method for rapidly generating the earth magnetic field.

2. Quick design technology for goods shelf type spacecraft structure

The prior modeling technology often relies on the understanding of professionals on three-dimensional shapes to construct models, and the mode can not meet the flexible and convenient use requirements of the current training task on the rapid design of the overall layout. Therefore, how to enable a user, especially a non-structural professional user, to complete the construction of a three-dimensional structure in a short time (several minutes) has become one of the key points and difficulties in the rapid design of a spacecraft structure. Therefore, in order to achieve the aim of simplified geometric modeling, the rapid design technology of the shelf type spacecraft structure extracts the three-dimensional structure of typical components for digitization by summarizing and summarizing the three-dimensional characteristics of a common spacecraft platform and load, establishes general model templates and components, enables a user to select proper templates or components to a layout area through man-machine interaction, and drags and modifies partial parameters according to requirements, so that the rapid design of the spacecraft can be completed. The method can be divided into basic component construction, structural layout, installation, conflict detection, effect display and the like according to the implementation flow, and comprises a shelf element construction method and a spacecraft assembly method based on shelf elements.

(1) Goods shelf type element construction method

The shelf type element construction method is characterized by defining a group of geometric models capable of effectively describing design elements and providing corresponding construction methods and component libraries. In general, the geometric model information of elements in the shelf design is qualitative, namely, the relationships of topology, position, orientation and the like among functional surfaces are qualitative, meanwhile, the geometric model is not only the description of the result of the shelf design, but also the division of the structure and the function is realized, the prototype design is formed, and the design can be automatically transferred to the subsequent interaction process. Not only geometric features but also characteristic elements of working features, material features and the like which are important for subsequent interaction should be considered in the design. Therefore, the shelf type element construction combines the three-dimensional characteristics of the conventional common spacecraft platform and load, makes a characteristic model library of some common load and spacecraft platform, considers that all models cannot be exhausted, and simultaneously adds some simple shape models such as spheres, cylinders and the like for adapting to construction requirements of some novel models, and supports users to quickly generate abstract load, part characteristic models and spacecraft in an interactive mode.

The result of the framework element construction can be used for auxiliary analysis, simulation analysis and the like of a training task scene, so that each designed geometric model comprises geometric topological features and various attributes such as material features. Therefore, detailed analysis is required to be carried out on the characteristics of the structural components of the spacecraft, and definition and classification in the current training field are summarized and summarized, and the characteristics can be primarily classified into shape characteristics, working characteristics (coverage analysis, shielding analysis and communication analysis), material characteristics (rendering, mechanical analysis and thermal analysis) and the like.

a) Shape feature

Considering the diversity of trial tasks and spacecraft loads, the shapes, structures, functions and assembly requirements of the various loads and the components are greatly different, and new loads which have never been designed before can be met. In the rapid design of a spacecraft, the expression of the load should be generalized, simplified and generalized as much as possible, and has a higher level of abstraction. Therefore, the detail which does not need to be focused in the training task can be ignored, and the training personnel can concentrate the attention to the most important and general common problems, so that the training task can be rapidly configured.

For long-term use in past tasks, the functions and shapes of the spacecraft load and the parts are relatively fixed, and a component characteristic model library formed by pre-summarizing and refining is provided for use, and editing functions such as triaxial zooming, rotation and the like are provided. The feature model library stores the shape features of the load, and also stores the material features and the working features of the load. Common loads and components like this are solar panels, lithium ion battery boxes, star sensors, star computers, GPS receivers, spray heads, various transmitting and receiving antennas, etc.

For the load and the component which are unique and novel in design, the load and the component belong to the first design, and can be replaced by a simple geometric model, and other characteristics can be input according to the requirement. Another way in the construction of shelf elements is to represent the satellite load with some simple representation shapes that are predefined and to assist in the display in colors, text, parameters, etc. These simple expression shapes may be cubes, rectangular parallelepiped, cylinders, round bars, spheres, etc., as shown in the following figures. It can be seen that the simplified model representation can meet the requirements of the novel spacecraft design, simplify the expression and improve the modeling and design speed.

In addition, in order to increase the diversity of the load and the components, the shelf type element construction also provides a solid modeling function to obtain the load expression through intersection, parallel and difference operation. However, in the practical structural design of the spacecraft, in order to improve the communication efficiency and the design speed, a simple and generalized expression mode is advocated to be used as much as possible. On the basis of meeting design expression, the design efficiency is improved.

b) Working characteristics

Spacecraft payloads have a particular shape of operational characteristics, for example an optical camera may operate in a linear scanning fashion, or may be probed with a pyramid field of view, while the operational range of the communication device may be a cone field of view. The operating characteristics of the load can be defined as: the effective load is taken as a sphere center, and a body surrounded by a conical surface with the effective distance as a radius is detected. Several possible operational features are shown in fig. 3 (a) -3 (c), where fig. 3 (a) is a linear scan field of view schematic fig. 3 (b) is a pyramid field of view schematic, and fig. 3 (c) is a cone field of view schematic:

The linear scanning operation is characterized in that an image acquired at a moment of a sensor is a line, the line array direction is perpendicular to the navigation direction, and one image is formed by splicing a plurality of images, so that the linear scanning operation is also called push-broom scanning imaging. The directors of the pyramid's operational features are a quadrilateral, which typically represents a dark matter particle detection satellite. The conical working characteristics are that the quasi-line of the visual conical surface is elliptical, such as an X-ray telescope spectroscope, a Leyman alpha coronagraph and the like which are commonly used in solar physics.

The shelf type element is constructed to define the shape of the load and add a working characteristic to the load according to requirements so as to assist in the design of the track and the gesture. In addition, simple analysis can be performed using the operating characteristics, for example, to determine if other loads or components are present that interfere with the field of view of the optical camera or the communication of the antenna.

c) Characteristics of materials, quality, etc

The shelf element construction also provides parameterized editing mode input load and material characteristics, quality characteristics and the like of the component, and is compounded with shape characteristics. The material characteristics can be used for simulation analysis or effect presentation and can be exported into a file to realize connection with other professional design software. And the quality features can be used for whole star quality estimation to evaluate whether the design meets quality constraints.

A feature model library is built by a pre-refined typical component model or a simple definition model of the design, and a shelf type element organization schematic formed by tree structure organization is shown in figure 4.

(2) Spacecraft assembly method based on components

The spacecraft assembly method based on the components adopts a structure design mode from bottom to top, is similar to the production process of factories, and is characterized in that the three-dimensional design of the components is carried out first, and then the components are assembled step by step to complete the assembly of the whole structure. The interactive assembly interface is shown in fig. 5, which is the following procedure:

a) Firstly, a blank design scene is established.

b) Platform types, such as rod type structures, plate type structures, central bearing cylinder structures, shell structures and the like, are selected from the left side assembly columns, and the size and the dimension of each part are adjusted. FIG. 6 is a schematic view of a platform assembly;

c) The internal load components are selected from the left component column and interactively set in size, weight, and other parameters.

d) And (3) installing the load in the platform, performing simple collision detection and adsorption, setting the installation posture of the load, and determining the size and the direction of a load visual field.

e) And (3) mounting external load of the platform, adjusting characteristic parameters such as size, weight, material and the like, setting the size and the direction of a detection view field, selecting the type of a turntable, and mounting and setting a movement mode.

f) The type of communication antenna, the manner of installation and the location of installation are selected.

g) The type of solar sailboard is selected, and the installation position and the unfolding mode are set.

h) Other types of components are installed.

i) And (3) finishing structural design and uploading design results. The above steps can be repeated if desired.

3. Task track rapid design technology based on characteristics

The traditional track design process is as follows: firstly, knowing a target, then designing a track according to the task target, and after finishing one-time track design, judging whether the requirement of the target can be met; if not, the improved design is carried out until the requirements are met. The process is repeated for a plurality of times, and the design process is complex. It is difficult to meet the requirements for rapid and convenient track design in space trial tasks.

The task track rapid design technology based on the characteristics is based on the task track requirement of space trial training, and the design process and the result feedback display process are required to have real-time performance, namely, when the user design is completed, track data and track preview are correspondingly changed, so that higher requirements are put forward on the efficiency and real-time performance of the track calculation model. The characteristic that the track design and the calculation complexity are unpredictable in an actual task is considered, and the track calculation model is designed into a multi-precision multi-level circulation recursion working mode. Fitting or approximating orbit data is adopted when the operation change of the orbit design is responded in real time, and after the operation is reduced and the design tends to be stable, the orbit dynamics model is continuously called for recursion accurate calculation until the accuracy meets the set error requirement.

The rapid task track design technology based on the characteristics is realized by directly operating the track on the screen by a user, and after the user changes the track on the screen, the background rapidly gives out the changed track parameters. Compared with the traditional track design, the graphical interactive mode has the characteristics of intuitiveness, convenience and high efficiency. The graphical interactive track design is performed in the following two steps.

First, a three-dimensional virtual space and celestial bodies are established, a reference system is provided for the track, and the operation of the track by a user is described in the reference space. The reference space adopts a J2000 coordinate system as a reference coordinate system, and a reference coordinate system commonly used in conventional satellite design is established in the system in advance. The user only needs to acquire the corresponding coordinate system from the system in a clicking mode, meanwhile, the user can also establish the coordinate system based on a specific mode, and the system can maintain the conversion relation between the user coordinate system and the common coordinate system. Then, the celestial bodies in the solar system are built in the built virtual space, and the positions and the speeds of the celestial bodies need to be supported by the accurate ephemeris. In addition, the rotation of the celestial body also needs to be accurately established, and the celestial body needs to be subjected to longitude and latitude division. Ephemeris for celestial bodies may be implemented using DE405 or DE435 ephemeris.

Secondly, the task track is quickly established or adjusted through the track feature points. A default track needs to be established first in order to provide the user with an object of operation. The user may establish a default track by drawing directly on the screen, clicking from a background database, entering parameters, etc. After the default track is established, the track characteristic points reflecting the current track measurement information are displayed in a striking mode, and the adjustment of the track by a user is completed by adjusting a series of characteristic points on the track. As shown, the user may click on any of the feature points and then drag them to change the shape and orientation of the track until the track can cover the task objective that the user needs to complete. The system extracts input information required by track root number calculation by utilizing the relative relation between the track characteristic points, the central celestial body and the virtual three-dimensional space, and completes the rapid calculation of the track root number. When the user changes the feature point positions, other feature points are changed correspondingly, so that the changed track accords with the real track characteristics. After the user completes the fast orbit design, the system should store the visualized design results in a way that the visualized design results are converted into the satellite orbit number. The specific calculation procedure is as follows.

As shown in fig. 7, a fast track construction diagram based on feature points is shown; after the user finishes drawing a track on the screen, the system can quickly calculate coordinate values of four reference points, wherein the coordinate values are in a reference system of J2000 inertial coordinate system (in the case of the earth being the center, the J2000 coordinate system of the earth and in the case of other celestial bodies being the center, the inertial coordinate system of the corresponding celestial body). Let the coordinates of four reference points be respectively

A-P _A ＝(x _A y _A z _A )

B-P _B ＝(x _B y _B z _B )

C-P _C ＝(x _A y _A z _A )

D-P _D ＝(x _A y _A z _A )

The center point of the coordinate point is the center of a J2000 inertial coordinate system. The distances from the four reference points to the center point are

The far and near sites of the target track are respectively

r _a ＝d _B ,r _p ＝d _A

The semi-long axis of the target track is

When the track is a circular track, the track radius is equal to the semi-major axis of the track, i.e

R＝r _a ＝r _p

Wherein R is the radius of the circular orbit.

The eccentricity of the target track is

When the track is a circular track, the eccentricity is zero, i.e. e=0.

The track inclination angle of the target track is complicated to calculate, firstly, the value of the normal vector of the track under the inertial coordinate system is calculated, namely

H＝(h _x h _y h _z ) ^T ＝P _A ×P _C ＝P _C ×P _B ＝P _B ×P _D ＝P _D ×P _A

Using the track normal vector, the track tilt i can be calculated as follows

Where H represents the modulus of the track normal vector H. This formula can also be used to calculate the inclination of the track when it is a circular track.

Calculation of the right ascent point first requires finding the intersection of the track plane and the equatorial plane. There are two such intersections, namely a rising intersection and a falling intersection. The intersection point is a lifting intersection point and a falling intersection point which need to be specified by a user, namely the track running direction desired by the user. According to the user's request, select the rising intersection point, assume as the D point. Finding coordinate points with zero Z-direction near the D point, i.e. P _a (x _a ,y _a ,z _a =0) (see figure), this point is the rising intersectionAnd (5) a dot. The included angle between the line of the intersection point and the coordinate center and the x axis of the inertial coordinate system is the right ascent point, and the calculation process is that

In the formula, ||P _a The expression vector P _a Is a mold of (a). The above formula is also applicable to calculating the right ascent and descent points of circular tracks.

The perigee amplitude angle is the included angle corresponding to the arc section from the perigee to the rising intersection point. Of the four reference points, the point a is near, and then the near argument can be calculated by the following equation.

In the method, in the process of the invention, the terms represent the modulus of the vector. When the track is a circular track, the track has no division of the far and near places, so that the number of the amplitude angles of the near places is not increased.

Five parameters of six tracks are calculated, and the position of the target track in the inertia space can be completely determined through the five parameters. The sixth parameter in the six parameters is the true near point angle, which characterizes the relative position of the satellite in orbit, and the true near point angle f of the satellite can be determined by the position of the user dragging the satellite in orbit.

After the rapid track number calculation is completed, if the user wants to obtain an accurate track number, the calculation of track data in the Cartesian coordinate system is required. At this time, the number of the tracks needs to be converted into track parameters under a Cartesian coordinate system, and then the track parameters under the Cartesian coordinate system are used for recursive calculation to obtain more accurate tracks. The calculation was performed according to the following conversion procedure:

a. calculating the current earth center distance

b. Calculating the amplitude angle of the current satellite

u＝ω+f

c. Calculating three components x, y, z of the current satellite position

d. Fig. 8 shows the relationship of satellite positions on celestial spheres. Wherein the s point is the projection of the satellite on the celestial sphere. From spherical trigonometric relationship

e. Calculating the current satellite velocity v

f. Calculating the component of velocity

The satellite velocity direction is in the orbital plane, which is set to point to the s' point in the figure. The included angle between s' and s is

|r×v|＝h

I.e.

From the tangential direction of the orbit ellipse, it can be judged that, at I, II quadrant f,in quadrant I; f in quadrant III, IV, < >>In quadrant II.

Order theCan be obtained by using spherical triangle formula

After the calculation of the orbit parameters in the Cartesian coordinates is completed, the orbit parameters can be used for calculating orbit data, namely orbit recursion, and a recursion formula is shown as follows.

Wherein x, y and z are satellite coordinates;distance from satellite to earth center; mu is the gravitational constant.

The technical effects of the system of the invention are as follows:

1) Fast generation of celestial body earth surface

The fast generation of celestial body surface includes fast generation of celestial light background, solar celestial body, celestial body surface environment, etc.

The rapid generation of the sky light background realizes the generation and drawing of constellation, star system, star cloud and the like based on the data of the published star tables such as the ibau star table, the SAO table and the like, and fig. 9 is a generation effect diagram of the sky light background.

Solar system celestial body rapid generation solar system planets and satellites are driven to move according to real ephemeris data to form a solar system celestial body movement scene, and fig. 10 is a solar system celestial body generation effect diagram.

The celestial body surface environment is rapidly generated as the earth surface environment, the topography and the relief are realized by adopting a texture mapping mode based on multi-resolution geographic data, the atmospheric effect is generated and rendered based on a single scattering model, and an effect map is generated by the earth in multi-resolution mode in FIG. 11.

2) Spatial environment rapid generation

The rapid generation of the space environment comprises the rapid generation of environmental elements which influence the operation of the spacecraft, such as an earth magnetic field, a radiation band, solar wind and the like.

The earth magnetic field is obtained by calculating the magnetic field intensity according to the position by adopting an international reference geomagnetic field or T96 magnetic layer magnetic field mode based on a magnetic line tracking method, and fig. 12 is an earth magnetic field effect diagram.

The earth radiation band is characterized by adopting an outermost layer fusion section method based on an electron AE8 and proton AP8 radiation band mode to form a visual effect, and fig. 13 is a section visual effect diagram based on radiation band data.

The solar wind forms the solar wind interplanetary magnetic field effect by adopting a magnetic force line tracking mode based on data sampling, and fig. 14 is a solar wind interplanetary effect diagram.

3) Quick interactive generation and design of goods shelf type spacecraft structure

The conventional common load and spacecraft platform is refined or a simple shape model is built to manufacture a characteristic model library, shelf elements are formed, a target spacecraft is quickly built through operations such as drag type pointing, zooming and the like, and fig. 15 is a rapid design effect diagram of a shelf type spacecraft structure.

4) Feature-based task track rapid interaction generation and design

The number of the tracks is changed by adopting a mode of drag track interaction design so as to quickly form a new track: according to six number setting feature points of the elliptic orbit, the interactive design of the orbit is realized by changing the feature points through mouse dragging, meanwhile, related numerical values can be directly changed through six number setting panels, and fig. 16 is a rapid design effect diagram of the task orbit based on the features.

Finally, it should be noted that the above embodiments are only for illustrating the technical solution of the present invention and are not limiting. Although the present invention has been described in detail with reference to the embodiments, it should be understood by those skilled in the art that modifications and equivalents may be made thereto without departing from the spirit and scope of the present invention, which is intended to be covered by the appended claims.

Claims (10)

1. A large scale space trial training task scenario rapid generation system, the system comprising:

the task training environment generation module is used for generating a task training environment through space environment data or a calculation mode;

the spacecraft generation module is used for constructing shelf type elements and generating different spacecraft based on the combination of the shelf type elements in a man-machine interaction mode;

the task track generation module is used for generating a task track in a graphical interactive mode; and

and the training task scene generation module is used for fusing the task training environment, the spacecraft and the task orbit to form a training task scene.

2. The rapid generation system of a large scale space trial training task scenario of claim 1, wherein in the task training environment generation module, generating a task training environment comprises: generating an earth magnetic field, generating an earth radiation band and generating solar wind; wherein the earth's magnetic field comprises an endogenous field and an exogenous field;

the generating an earth magnetic field includes: calculating an intrinsic field by adopting an international standard 'international reference geomagnetic field' in geophysics, and calculating an extrinsic field by adopting a T96 magnetic layer magnetic field mode; and the magnetic force lines are adopted to characterize the earth magnetic field;

The generating an earth radiation band comprising: calculating an earth radiation band by adopting an electron AE8 mode and a proton AP8 mode, and carrying out the calculation by adopting a mode of fusing an outermost layer, and representing the earth radiation band by carrying out visual representation on the distribution condition of omnidirectional integral fluxes of protons and electrons with different energies in the radiation band in space;

the generating solar wind includes: simulating the density, temperature, speed and magnetic field distribution of the solar wind plasma in space according to the existing observation data within the space range of 1AU, wherein the density and the temperature are described by only one data item; the speed and the magnetic field strength are required to be determined by components in the directions of 3 coordinate axes; the method is characterized in that the density or the temperature is represented by converting a data item into a color based on a color table, and the representing effect of speed and magnetic field intensity is generated by interpolation in solar wind data by adopting a magnetic line generation mode in a method for rapidly generating the earth magnetic field.

3. The rapid generation system of a large-scale space training task scenario according to claim 2, wherein the calculation formulas of the north component X, the east component Y and the vertically downward component Z of the endogenous field are respectively:

Wherein, (r, θ, λ) is the geocentric coordinates, r is the geocentric distance, θ is the geographic residual latitude; λ is the geographic longitude, a is the earth radius,and->Is a Gaussian coefficient of a certain order N at time t, < >>Is an n-order m-order Schmidt quasi-normalized Legendre function;

the T96 magnetic layer magnetic field mode is to calculate an external magnetic field at a certain point in space by using solar wind pressure, DST index, inter-planetary magnetic field and geomagnetic inclination angle;

the magnetic field of the earth is characterized by magnetic lines of force, and the method specifically comprises the following steps: determining an initial position point P1 of magnetic force lines, advancing to P2 in the magnetic field direction by a small step length T according to the magnetic field intensity of the point, and repeating the process at the point P2 until reaching the boundary of a data field or other termination conditions; the magnetic field intensity of any point P is calculated by adopting an international reference geomagnetic field or T96 magnetic layer magnetic field mode according to the position of the magnetic field intensity;

when simulating the distribution condition of the density, the temperature, the speed and the magnetic field of the plasmas of the solar wind in space, sampling the data of the solar wind in space in the polar coordinate space, and specifically comprises the following steps:

the reference coordinate axis of the solar yellow track coordinate system is marked by an x axis, a y axis and a z axis, and the reference coordinate axis is marked byDetermining the spatial position of each sampling point by ternary method, r 'is the distance from the sampling point to the sun center, θ' is the angle between the projection of the sampling point and the center line in the yellow road surface and the x-axis of the yellow road coordinate system of the sun center,/and%>Is the included angle between the connecting line of the sampling point and the sun center and the z axis of the coordinate system of the yellow track of the sun center; the attribute field for each sample point includes: background field density, background field temperature, particle density at a certain simulation time, temperature, magnetic field strength and radial velocity; the closer to the centroid the data sampling frequency per unit distance is, the higher the sampling.

4. The rapid generation system of a large scale space training mission scenario of claim 1, wherein in the spacecraft generation module, constructing shelf elements comprises: summarizing and summarizing three-dimensional characteristics of each spacecraft platform and load, extracting a three-dimensional structure of a typical part for digitizing, defining a geometric model, establishing a model template and a module, and providing a corresponding construction method and a module library; wherein,

defining geometric topological features, shape features, working features, material features and quality features of the geometric model; when defining the working characteristics, at least performing coverage analysis, shielding analysis and communication analysis on the components; at least the rendering analysis, the mechanical analysis, and the thermal analysis are performed on the part when defining the operational characteristics.

5. The rapid generation system of a large-scale space training task scene according to claim 1, wherein in the spacecraft generation module, when different spacecrafts are generated based on the combination of shelf elements in a man-machine interaction mode, a structural design mode from bottom to top is adopted, three-dimensional design of components is firstly carried out, then the components are assembled step by step, and the assembly of the whole spacecraft structure is completed, and the rapid generation system specifically comprises:

a) Establishing a blank design scene;

b) Selecting the type of a spacecraft platform, and adjusting the size of each part of the spacecraft platform;

c) Selecting an internal load component of the spacecraft, and adjusting parameters including size and weight;

d) The method comprises the steps of installing and detecting the internal load of a platform, including collision and adsorption, setting the installation posture of the load at the same time, and determining the size and the direction of a load visual field;

e) The external load of the mounting platform is adjusted, characteristic parameters including size, weight and material are adjusted, the size and the direction of a detection view field are set, the type of a turntable is selected, and a movement mode is installed and set;

f) Selecting a communication antenna type, an installation mode and an installation position;

g) Selecting a solar sailboard type, and setting an installation position and an unfolding mode;

h) And (5) completing the structural design of the spacecraft.

6. The large scale space trial training task scenario rapid generation system of claim 1, wherein the task trajectory generation module comprises: a space generating unit, a celestial body generating unit, a track calculating and adjusting unit, wherein,

the space generating unit is used for establishing a three-dimensional virtual space and a reference coordinate system;

the celestial body generating unit is used for establishing celestial bodies in the solar system in the three-dimensional virtual space, including the position, the speed and the rotation of the celestial bodies, and dividing the celestial bodies into longitude and latitude;

the track calculation and adjustment unit is used for establishing, adjusting and generating a task track in the three-dimensional virtual space through the track feature points.

7. The rapid generation system of a large-scale space training task scene as defined in claim 6, wherein the track calculation and adjustment unit establishes, adjusts and generates a task track in a three-dimensional virtual space through track feature points, and comprises:

establishing a default track as an operation object in a mode of directly drawing on a screen, clicking or inputting parameters from a system background database, wherein when the default track is directly drawn and established on the screen, the relative relation between the track characteristic points, a central celestial body and a virtual three-dimensional space is utilized to extract input information required by track root number calculation, and the calculation of the quick track root number is completed;

After the default track is established, the shape and the azimuth of the track are changed by adjusting a series of track characteristic points reflecting the current track measurement information on the track until the track can cover the adjustment of the track of the task target which is required to be completed by the user, and a task track is generated.

8. The rapid generation system of large scale space training task scenarios of claim 7, wherein in completing the calculation of the rapid orbit root, when the orbit is an elliptical orbit, the calculated orbit root comprises: the semi-long axis a, the eccentricity e, the track inclination angle i, the near-place radial angle omega, the rising intersection point right ascent angle omega and the true near-point angle f are calculated as follows:

wherein r is _a ,r _p The far and near spot radii of the target track are respectively represented: r is (r) _a ＝d _B ,r _p ＝d _A ；d _j Representing the distance from the reference point j to the center point; (x) _j ，y _j ，z _j ) Representing the coordinate P of the reference point j _j ；

Wherein H represents the modulus of the track normal vector H;

H＝(h _x h _y h _z ) ^T ＝P _A ×P _C ＝P _C ×P _B ＝P _B ×P _D ＝P _D ×P _A ，(h _x h _y h _z ) Representing a track normal vector;

wherein O is the center of coordinates, P _a (x _a ,y _a ,z _a =0) is the intersection of the rises, ||op _a The I represents the mode of the vector of the line connecting the ascending intersection point and the coordinate center;

in the method, in the process of the invention, the terms represent the modulus of the vector;

the true near point angle f is determined by the position in orbit of the user dragging the satellite.

9. The rapid generation system of a large-scale space training task scene as defined in claim 8, wherein in the track calculation and adjustment unit, the task track is established, adjusted and generated in the three-dimensional virtual space through the track feature points, and further comprising: after the rapid track number calculation is completed, the track number is converted into track parameters under a Cartesian coordinate system, and then the track parameters under the Cartesian coordinate system are used for recursive calculation, so that a more accurate track is obtained.

10. The rapid generation system of large scale space trial training task scenarios of claim 9, characterized in that the translating the number of trajectories to trajectory parameters in a cartesian coordinate system comprises:

a) Calculating a current ground center distance r:

b) Calculating the amplitude angle u of the current satellite:

u＝ω+f

c) Three components x, y, z of the current satellite position are calculated:

wherein, the s point is the projection of the satellite on the celestial sphere, r is the earth center distance, i is the orbit inclination angle, u is the amplitude angle of the current satellite, and Ω is the right ascent intersection point;

d) Calculating the current satellite rate v:

wherein μ is the gravitational constant;

e) Calculating the component of velocity

Wherein,s' represents the pointing point of the satellite velocity direction in the orbital plane, and m represents one derivation; the angle between s' and s satisfies:

f at the I, II quadrant number,in quadrant I; f in quadrant III, IV, < >>In quadrant II.

When the track parameters under Cartesian coordinates are used for recursive calculation, a recursive formula is as follows:

wherein x, y and z are satellite coordinates, and represent secondary derivation;is the distance from the satellite to the earth center.