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

A rapid generation system for large-scale spatial trial training task scenarios

Technical field

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

Background technique

Currently, military training is faced with practical training difficulties such as novel and unique combat modes, dynamic changes in combat objects, and complex and diverse combat conditions. Considering that the most realistic military operation in a peaceful environment is exercise training, if combat trials are carried out in combination with exercise training , not only can meet the needs of "actual combat", but will also significantly reduce training costs to ensure training safety without interfering with the actual system.

With the continuous development of informatization construction in the field of experimental training, military training has moved deeper into actual combat, which is reflected in the expansion of test objects into equipment systems, the transformation of test environments into complex environments, and the transformation of test models into integrated joint efforts. Through simulation, a trial training system close to actual combat is built to support the troops in carrying out post operation training, system confrontation training and other activities. It not only facilitates the flexible layout of training scenarios, enriches training content, but also effectively improves training effects.

The task scenario construction of the trial training system must not only comply with the characteristics of space trial training methods such as diverse means, complex systems, and numerous elements, but also need to flexibly set training scenario parameters to construct different training scenario content to meet the requirements of job operation training, tactical tactics research, etc. . During the construction of the trial training scenario, in addition to quickly constructing the spacecraft structure and designing the mission orbit, more importantly, the space environment has an important impact on the spacecraft's orbit design and control, equipment safety, mission planning and other aspects at all times. Space environments such as magnetic fields, radiation belts, solar wind, etc. may have varying degrees of impact and damage on spacecraft communications, energy, structure, electronic equipment, load performance, etc.

At present, the trial training system rarely considers the introduction and impact of factors such as the space environment. Even if it is involved, a certain type of environmental factors is introduced from the perspective of front-end display, which is far from meeting the actual environmental simulation requirements. At the same time, the construction of mission scenarios such as mission orbits and spacecraft structures is carried out in a parametric form through template matching or user input. This method is neither intuitive and simple nor can it meet the needs of rapid construction.

To sum up, in a trial training system oriented to complex environments and system confrontations, quickly constructing large-scale, flexible, and realistic trial training task scenarios is the foundation and core of training tasks, and it is also a huge challenge.

Contents of the invention

The purpose of the present invention is to solve the problems surrounding the difficulty of quickly generating large-scale real trial training task scenarios in the field of space trial training. This invention breaks through key technologies such as rapid construction of environmental elements for trial training missions, rapid design of shelf-type spacecraft structures, and rapid design of mission orbits based on characteristics, and realizes the construction of real and flexible trial training mission scenarios in large-scale space, which provides training Provide technical support for exercises and training under simulation and research on tactics and tactics.

The main purposes of the present invention specifically include:

1. Greatly enhance the flexibility of spacecraft structure and orbit design, thereby expanding the freedom of troop deployment in training scenarios, and effectively improving scenario construction and training efficiency.

2. Promote the development of the trial training system that integrates the impact of the space environment, so that the trial training system can develop in a direction that is closer to reality.

In order to achieve the above objects, the present invention is achieved through the following technical solutions.

The present invention proposes a large-scale space trial training task scene rapid generation system. The system includes:

The task training environment generation module is used to generate the task training environment through spatial environment data or computing models;

The spacecraft generation module is used to build shelf-type elements, and use human-computer interaction to combine and generate different spacecrafts based on the shelf-type elements;

A mission trajectory generation module for generating mission trajectories in a graphical and interactive manner; and

The trial training mission scenario generation module is used to integrate the mission training environment, spacecraft and mission orbit to form a trial training mission scenario.

As one of the improvements of the above technical solution, in the mission training environment generation module, generating the mission training environment includes: generating the earth's magnetic field, generating the earth's radiation belts and generating the solar wind; wherein the earth's magnetic field includes the internal source field and the external source field;

The generation of the earth's magnetic field includes: using the international standard "International Reference Geomagnetic Field" in geophysics to calculate the internal source field, using the T96 magnetospheric magnetic field model to calculate the external source field; and using magnetic field lines to characterize the earth's magnetic field;

The generation of the earth's radiation belt includes: using the electron AE8 and proton AP8 modes to calculate the earth's radiation belt, and using the outermost fusion cross-section method to calculate the omnidirectional direction of protons and electrons with different energies in the radiation belt in space. Visual representation of the distribution of integrated flux to characterize the Earth's radiation belts;

The generation of solar wind includes: simulating the density, temperature, velocity and magnetic field distribution of plasma in the solar wind within a 1AU spatial range based on existing observational data, wherein density and temperature are described by only one data item; velocity and magnetic field strength need to be determined by the components in the three coordinate axis directions; and a data item is converted into color based on the color table to characterize the density or temperature, using the magnetic field line generation method in the earth's magnetic field rapid generation method, through the solar wind data Medium interpolation generates characterization effects on velocity and magnetic field strength.

As one of the improvements to the above technical solution, the calculation formulas of the northward component X, eastward component Y and vertical downward component Z of the internal source field are respectively:

Among them, (r, θ, λ) is the geocentric coordinate, r is the geocentric distance, θ is the geographical colatitude; λ is the geographical longitude, a is the radius of the earth, and/> is the Gaussian coefficient of a certain order N at time t,/> is the m-order Schmidt quasi-normalized Legendre function of order n;

The T96 magnetospheric magnetic field model uses solar wind pressure, DST index, interplanetary magnetic field and geomagnetic inclination to calculate the external magnetic field at a certain point in space;

The use of magnetic field lines to characterize the earth's magnetic field specifically includes: determining the initial position point P1 of the magnetic field lines, advancing to P2 with a small step size T in the direction of the magnetic field according to the magnetic field strength at this point, and repeating the above process at point P2 until Reach the boundary or other termination conditions of the data field; the magnetic field strength of any point P is calculated based on its location using the international reference geomagnetic field or the T96 magnetospheric magnetic field model;

When simulating the density, temperature, velocity and magnetic field distribution of solar wind plasma in space, the space solar wind data is sampled in polar coordinate space, specifically including:

The reference coordinate axes of the solar ecliptic coordinate system are identified with the x-axis, y-axis and z-axis, as given by The ternary formula determines the spatial position of each sampling point. r' is the distance from the sampling point to the heliocenter of the sun. θ' is the intersection between the projection of the line connecting the sampling point and the heliocenter in the ecliptic plane and the x-axis of the heliocentric ecliptic coordinate system. angle,/> It is the angle between the line connecting the sampling point and the heliocenter and the z-axis of the heliocentric ecliptic coordinate system; the attribute domain of each sampling point includes: background field density, background field temperature, and particle density, temperature, and magnetic field intensity at a certain simulation moment and radial velocity; when sampling, the closer to the heliocenter, the higher the data sampling frequency per unit distance.

As one of the improvements to the above technical solution, in the spacecraft generation module, building shelf elements includes: summarizing and summarizing the three-dimensional characteristics of each spacecraft platform and payload, extracting the three-dimensional structure of typical components for digitization, defining geometric models, and establishing Model templates and components and provide corresponding construction methods and component libraries; among them,

When defining the geometric model, include defining the geometric topological characteristics, shape characteristics, work characteristics, material characteristics and quality characteristics of the geometric model; when defining the work characteristics, at least perform coverage analysis, occlusion analysis and communication analysis on the components; when defining the work characteristics, at least Perform rendering analysis, mechanical analysis, and thermal analysis on components.

As one of the improvements to the above technical solution, in the spacecraft generation module, when different spacecrafts are generated based on human-computer interaction based on shelf-type elements, a bottom-up structural design mode is adopted, and the three-dimensional design of the components is first carried out. The components are then assembled step by step to complete the assembly of the entire spacecraft structure, including:

a) Establish a blank design scene;

b) Select the type of spacecraft platform and adjust the size of each part of the spacecraft platform;

c) Select the spacecraft’s internal load components and adjust parameters, including size and weight;

d) Install and detect the internal load of the platform, including collision and adsorption, while setting the installation posture of the load and determining the size and direction of the load field of view;

e) Install the external load of the platform, adjust the characteristic parameters, including size, weight and material, set the size and direction of the detection field of view, select the turntable type, install and set the movement mode;

f) Select the communication antenna type, installation method and installation location;

g) Select the solar panel type, set the installation position and deployment method;

h) Complete the spacecraft structural design.

As one of the improvements of the above technical solution, the mission orbit generation module includes: a space generation unit, a celestial body generation unit, an orbit calculation and adjustment unit, wherein,

The space generation unit is used to establish a three-dimensional virtual space and establish a reference coordinate system;

The celestial body generation unit is used to establish celestial bodies in the solar system in a three-dimensional virtual space, including the position, speed and rotation of the celestial bodies, and divide the celestial bodies into longitude and latitude;

The orbit calculation and adjustment unit is used to establish, adjust and generate mission orbits in a three-dimensional virtual space through orbit feature points.

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

Establish a default orbit as the operation object by directly drawing on the screen, clicking from the system background database, or inputting parameters. When drawing directly on the screen to establish the default orbit, the orbit feature points and the central celestial body, The relative relationship in the virtual three-dimensional space extracts the input information required for orbit root number calculation to complete the calculation of fast orbit root number;

After the default orbit is established, the shape and orientation of the orbit are changed by adjusting a series of orbit feature points on the orbit that reflect the current orbit metric information until the orbit can cover the mission goals that the user needs to complete. The adjustment of the orbit is completed and the mission orbit is generated.

As one of the improvements to the above technical solution, in the process of completing the calculation of the fast orbit root number, when the orbit is an elliptical orbit, the calculated orbit root number includes: semi-major axis a, eccentricity e, orbit inclination angle i, and perigee argument ω, ascending node right ascension Ω and true periapsis angle f, the calculation formulas are respectively:

Among them, r _a and r _p represent the far and perigee radii of the target orbit respectively: r _a =d _B ,r _p =d _A ; d _j represents the distance from the reference point j to the center point; (x _j , y _j , z _j ) represents the coordinate P _j of the reference point j;

In the formula, ||H|| represents the module of the orbit normal vector H;

H=(h _x h _y h _z ) ^T =P _A ×P _C =P _C ×P _B =P _B ×P _D = _PD ×P _A , (h _x h _y h _z ) represents the orbit normal vector;

In the formula, O is the coordinate center, P _a (x _a , y _a , z _a = 0) is the ascending node, ||OP _a || represents the module of the vector connecting the ascending node and the coordinate center;;

In the formula, ||·|| represents the module of the vector;

The true periapsis angle f is determined by the user dragging the position of the satellite in orbit.

As one of the improvements to the above technical solution, the orbit calculation and adjustment unit establishes, adjusts and generates mission orbits in a three-dimensional virtual space through orbit feature points. It also includes: after completing the calculation of fast orbit elements, converting the orbit elements into to the orbit parameters in the Cartesian coordinate system, and then use the orbit parameters in the Cartesian coordinate system to perform recursive calculations to obtain a more accurate orbit.

As one of the improvements to the above technical solution, the transformation of orbital radical numbers into orbital parameters in the Cartesian coordinate system includes:

f) Calculate the current geocentric distance r:

g) Calculate the argument u of the current satellite:

u=ω+f

h) Calculate the three components x, y, z of the current satellite position:

Among them, point s is the projection of the satellite on the celestial sphere, r is the geocentric distance, i is the orbital inclination, u is the argument of the current satellite, and Ω is the right ascension of the ascending node;

i) Calculate the current satellite rate v:

Among them, μ is the gravitational constant of the earth;

j) Calculate the components of velocity

in, The s′ point represents the pointing point of the satellite velocity direction in the orbital plane, and ˙ represents a derivation; the angle between s′ and s satisfies:

When f is in the I and II quadrants, In the I quadrant; when f is in the III and IV quadrants,/> In Quadrant II.

When performing recursive calculation using orbital parameters in Cartesian coordinates, the recursive formula is:

In the formula, x, y, z are satellite coordinates, and ¨ represents the quadratic derivation; is the distance from the satellite to the center of the earth.

Compared with the prior art, the advantages of the present invention are:

1. The system of the present invention realizes the rapid generation of typical elements of the space environment for trial training missions; in view of the impact of the space environment on the spacecraft during trial training missions, a rapid generation of typical elements that embodies the distribution rules, data connotations and changing characteristics of environmental elements is proposed. The generation method quickly calculates the full-space environment value through the environmental element model, which meets the requirements of the trial training task for full-time full-space value without having to be consistent with the objective world at all times. It basically meets the requirements of close to actual combat and has high application value. ;

2. The system of the present invention realizes the rapid generation of force structures and tracks in trial training scenarios; in view of the complex space trial training tasks, frequent scene creation and changes, and training personnel are often not professionals in structure or track, it is difficult to use professional tools problem, a method for rapid generation of spacecraft structures and orbits is proposed. Through shelf-type assembly or drag-and-drop characteristic orbit modification, it subverts the conventional design methods in the field of space trial training. It is a new applied research work with certain originality. Greatly improve the efficiency of field personnel.

Description of drawings

Figure 1 is a roadmap of three key technologies mainly involved in the rapid generation system of large-scale space trial training task scenarios;

Figure 2 is a schematic diagram of the spatial location of the solar wind sampling point;

Figure 3(a)-Figure 3(c) are schematic diagrams of several working characteristics. Figure 3(a) is a schematic diagram of a linear scanning field of view. Figure 3(b) is a schematic diagram of a pyramid field of view. Figure 3(c) is a schematic diagram of a cone field of view. schematic diagram;

Figure 4 is a schematic diagram of the organizational structure of shelf elements;

Figure 5 is a schematic interface diagram of the component-based spacecraft assembly method;

Figure 6 is a schematic diagram of the platform components;

Figure 7 is a quick construction diagram of an orbit based on feature points;

Figure 8 shows the spherical relationship of the satellite;

Figure 9 is a rendering of skylight background generation;

Figure 10 is a rendering of solar system celestial bodies;

Figure 11 is a multi-resolution rendering of the earth;

Figure 12 is a rendering of the earth’s magnetic field;

Figure 13 is a cross-section visualization rendering based on radiation belt data;

Figure 14 is an interplanetary rendering of solar wind;

Figure 15 is a rapid design rendering of the shelf-type spacecraft structure;

Figure 16 is a quick design rendering of a task track based on features.

Detailed ways

The technical solution of the present invention will be described in detail below with reference to the accompanying drawings and examples.

The invention relates to a trial training mission scene generation system, and in particular to a rapid generation system for space environment, spacecraft and other scenarios under large-scale space confrontation trial training missions in the field of space trial training.

This patent designs a rapid generation system for space environment and spacecraft scenarios under large-scale space confrontation trial training missions. Its technical route is shown in Figure 1. To meet the demand for rapid generation of large-scale space trial training mission scenarios, firstly, the mission training environment is generated through space environment data or computing models. Secondly, different spacecrafts are generated based on the pre-built shelf products using human-computer interaction method, and then drag-and-drop adjustment is used. The mission trajectory is generated using a WYSIWYG method of orbit feature points taking into account the influence of environmental factors. Finally, a trial training mission scenario is formed through the fusion of environmental and spacecraft data. Of course, space mission scenarios are inseparable from the construction of celestial bodies and surfaces, that is, the simulation and construction of skylight backgrounds, solar system celestial bodies, and celestial body surface environments. The skylight background construction can realize constellations based on data from public star catalogs such as the Ibagu star catalog and the SAO catalog. Generation and drawing of galaxies, nebulae, etc.; solar system celestial body simulation can drive the movement of solar system planets and satellites based on real ephemeris data to form solar system celestial body movement scenes; the surface environment of celestial bodies is constructed such as the earth's surface environment, and its topography and landforms are textured based on multi-resolution geographical data. Implemented through mapping, atmospheric effects are generated and rendered based on a single scattering model. Based on these basic scenarios, this patent mainly elaborates on the three key technologies involved: rapid construction technology of environmental elements for trial training missions, rapid design technology of shelf-type spacecraft structure, and rapid design technology of mission orbit based on characteristics.

1. Rapid construction technology of environmental elements for trial training tasks

With the rapid development of my country's aerospace applications, environmental information such as magnetic fields and radiation fields in the "near/near-Earth/deep space" space where the spacecraft is located has become increasingly important to the operation and safety of space missions. Space environment data involves various physical fields such as magnetic fields, gravitational fields, and solar wind in near-Earth space, solar-Earth space, and even interplanetary space. Data types include two-dimensional/three-dimensional scalars, vector fields, images, etc., and the reference coordinate system Complex and highly dynamic, through the rapid construction and expression of these large-scale multi-dimensional spatial environment information, on the one hand, the spatial distribution, movement rules and dynamic characteristics of the spatial environment can be intuitively displayed in front of people and directly perceived by human vision; on the other hand, On the other hand, through the three-dimensional visualization of the three-dimensional space of the space environment, combined with the analysis of space task requirements, it can provide auxiliary support for the simulation, training, and research of space tasks.

The spatial environment has the characteristics of large spatio-temporal scale span, complex reference coordinate system, large amount of environmental data with high dynamic changes, and difficulty in expressing non-visual information. It is currently very unrealistic to simulate it in real time and with high accuracy. At the same time, in the simulation of trial training tasks, it is not necessarily necessary to have a spatial environment that is completely consistent with the objective world. What is more important is to reflect the distribution rules, data connotations and changing characteristics of each type of environmental elements. This can promote training personnel's understanding of spatial environment knowledge. Understand, the perception of factors and the application of effects to improve the level of spatial environment cognition and training effects. Here we take the construction of typical space environments such as the Earth's magnetic field, radiation belts, and solar wind as examples to illustrate the rapid generation method.

(1) Rapid generation method of the earth’s magnetic field

The geomagnetic field is composed of various magnetic field components generated by magnetic rocks inside the earth and current systems distributed inside and outside the earth. According to its origin, it can be divided into internal source field and external source field. The geomagnetic field is a vector field that is a function of position in space and time.

In the rapid generation of the geomagnetic field, the internal source field is calculated using the "International Reference Geomagnetic Field" (IGRF), an international standard in geophysics. It is expressed in the form of a spherical harmonic series, the highest order of which is usually 10, with a total of 120 spherical harmonic coefficients. In the passive region of near-Earth space, the main magnetic field originating from the interior of the earth can be expressed as a negative gradient of the magnetic potential V, and V can be expanded into the form of a spherical harmonic function:

Among them, γ, θ, and λ are the geocentric coordinates (γ is the distance from the center of the earth; θ is the geographical colatitude, that is, 90-geographical latitude; λ is the geographical longitude), α is the radius of the earth, and/> is the Gaussian coefficient at time t,/> It is the Schmitt quasi-normalized Legendre function of order n and m. The international reference geomagnetic field assumes that the change in the main magnetic field within 5 years is a linear change. By changing the prediction coefficient and/> The changes in the main magnetic field in the next 5 years are given.

The relationship between magnetic field and magnetic potential is:

Therefore, the northward component X, the eastward component Y and the vertical downward component Z of the geomagnetic field are respectively

As long as the Gaussian coefficient is given, the three components of the basic magnetic field at any point can be obtained from the above expression. According to a large number of detection results, the Gaussian coefficient with a certain order N is obtained by fitting. and/> The three components of the above magnetic field can be calculated 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 expressions and the corresponding time coefficients.

Since the magnetic field generated by the magnetospheric current system in the space outside 6Re cannot be ignored, the rapid generation of the geomagnetic field from the external source field is calculated using the T96 magnetospheric magnetic field model that is currently widely used in the research of many space physics problems. The T96 magnetospheric magnetic field model is an empirical model obtained by analyzing and fitting 36,682 magnetic field vector observation data obtained by multiple satellites under different magnetic disturbance levels. These observations cover a considerable magnetospheric space. This magnetic field model is suitable for a spatial range of 4 to 70 Earth radii. It includes the main magnetic field and the magnetic field generated by the main magnetospheric current system. It uses solar wind pressure, DST index, interplanetary magnetic field and geomagnetic inclination to calculate the external magnetic field B=(Bx,By,) at a point in space (X, Y, Z). Bz) model. Bx is called the north component of the geomagnetic field, By is the east component of the geomagnetic field, and Bz becomes the vertical component of the geomagnetic field.

Magnetic fields are usually represented by magnetic field lines. The magnetic field line is a virtual curve that is tangent to the magnetic induction intensity everywhere. The direction of the magnetic induction intensity is consistent with the direction of the magnetic field lines, and its size is proportional to the density of the magnetic field lines. For the three-dimensional vector field of the magnetic field, P is one of the points, and its position is r. The magnetic field line passing through P is a space curve. As a function of t, r has

Solving this equation can construct an instantaneous field line.

Assuming that the field line is r(t)≡[x(t),y(t),z(t)] ^T , which is the solution of the equation, then the integral expression of the field line in the physical space is:

The above equation shows that the field lines are generated starting from an initial position with a small step size t, and r(0) is the initial condition. According to this idea, the basic principle for the generation of geomagnetic field lines is: determine the initial position P1 of the magnetic field lines, according to the magnetic field strength at that point, advance to P2 in the direction of the magnetic field with a small step size t, and repeat the above process at P2 until it reaches Boundaries or other termination conditions for data fields. The magnetic field strength at any point P is calculated using the international reference geomagnetic field or the T96 magnetospheric magnetic field model based on its location.

(2) Rapid generation method of Earth’s radiation belts

The Earth's radiation belt includes the inner radiation belt and the outer radiation belt. The center of the inner radiation belt is about 1.5 Re and the area between magnetic latitude ±40°. The outer radiation belt is at 3-4 Re and is about 6000 kilometers thick. The range can be extended. to the spatial range of 50° to 60° magnetic latitude. These areas are filled with a large number of high-energy charged particles. Observation statistics show that magnetic storms and strong substorms often cause serious malfunctions in satellites operating in the radiation belt area.

The particles in the radiation belts are mainly affected by the strong influence of the geomagnetic field. Under the influence of the geomagnetic field, the charged particles in the radiation belts make periodic motion on many drum-shaped surfaces called "magnetic shells". The L-B coordinate system is commonly used to describe the spatial distribution of particles in the radiation belts. B is the magnetic field strength at a specific point in space, in Gauss units; L is the magnetic shell parameter. For a specific magnetic shell in a certain place, L is a constant. Under the central dipole geomagnetic field approximation, L is the distance of the magnetic shell on the equatorial plane, which is measured in the Earth's radius Re.

The internationally popular radiation belt modes developed by NASA, namely the electron AE8 and proton AP8 modes, are used to rapidly generate radiation belts. This model is an average and static empirical model compiled based on satellite data. It gives the particle flux of electrons and protons in different energy ranges (0.1~400Mev) in the space range (1.15~6.6L). The spatial position is determined by B-L coordinates.

The characterization of the radiation belt is carried out by using the outermost fusion section, which visually represents the distribution of the omnidirectional integrated flux in space of protons and electrons with different energies in the radiation belt. Specifically, two sections along different longitudes and the outermost plane between these two sections are rendered. The surface color and transparency are represented by the proton or electron flux of the point in color, with each value corresponding to a color. Through the change of color, the change of flux size is expressed.

(3) Rapid solar wind generation method

The solar wind fills the entire interplanetary space of the heliosphere system and is formed and emitted from the corona, the outermost layer of the solar atmosphere. There are long-term large-scale dark areas in the corona, which are open areas of the solar magnetic field. The magnetic field lines here spread into the universe, and a large amount of plasma runs out along the magnetic field lines, forming a high-speed particle flow. When it reaches the vicinity of the Earth's orbit, , the speed can reach more than 300~400km per second. This high-speed plasma flow is what we call the solar wind. At present, there is no unified reference model for the changing laws of the solar wind. Therefore, the rapid generation method of solar wind is to simulate the density, temperature, velocity and magnetic field of the solar wind plasma within the 1AU (Sun-Earth distance) spatial range based on existing observation data. distribution in space. Among them, density and temperature are scalar fields, and this attribute can be described by only one data item; while speed and magnetic field strength are vector fields, and this attribute needs to be determined by components in the three coordinate axis directions.

The spatial domain of solar wind data is a sphere, and the spatial data needs to be sampled in polar coordinate space. As shown in Figure 2: the x-axis, y-axis and z-axis identify the reference coordinate axes of the solar ecliptic coordinate system, P is a certain sampling point in space, r is the distance from the sampling point P to the heliocentre of the sun, θ is The angle between the projection of the sampling point P and the heliocentric line in the ecliptic plane and the x-axis of the heliocentric ecliptic coordinate system, is the angle between the line connecting the sampling point and the heliocenter and the z-axis of the heliocentric ecliptic coordinate system, given by/> The ternary formula determines the spatial position of each sampling point P. The attribute domain of each sampling point includes: background field density, background field temperature, and particle density, temperature, magnetic field strength and radial velocity at a certain simulation moment. Within the spatial range with 1Au as the radius and the sun as the center, the spatial resolution of the data at each simulation moment is: 154*55*80. In view of the fact that the change rate of the attribute value of the sampling point decreases with the increase of the distance from the heliocentre, a non-uniform sampling method is adopted for data sampling - the closer to the heliocentre, the higher the data sampling frequency per unit distance. In terms of time resolution, the simulation data records the changes in solar wind attribute data over time for 50 consecutive hours, that is, at 100 simulation time points, with a time interval of 0.5 hours. At the speed of solar wind, 50 hours is enough for the high-energy particles ejected from the solar coronal hole to travel from the sun to the earth.

For the characterization of solar wind data, density and temperature are scalar fields, which can be described by converting a data item into a color based on a color table; while velocity and magnetic field strength are vector fields, which need to be determined by components in the three coordinate axis directions, using the The magnetic field line generation method in the earth's magnetic field rapid generation method can generate the solar wind vector field representation effect by interpolating in the solar wind data.

2. Rapid design technology of shelf-type spacecraft structure

In the past, modeling technology often relied on professionals' understanding of three-dimensional shapes to build models. This method can no longer meet the current trial training tasks' flexible and convenient use requirements for rapid overall layout design. Therefore, how to enable users, especially non-structural professional users, to complete the construction of three-dimensional structures in a short time (a few minutes) has become one of the key points and difficulties in the rapid design of spacecraft structures. Therefore, in order to achieve the goal of simplified geometric modeling, the rapid design technology of shelf-type spacecraft structures summarizes and summarizes the three-dimensional characteristics of common spacecraft platforms and loads, extracts the three-dimensional structures of typical components for digitization, and establishes common model templates and components. Users select appropriate templates or components to the layout area through human-computer interaction, and drag and modify some parameters according to needs to complete the rapid design of the spacecraft. According to the implementation process, it can be divided into basic component construction, structural layout, installation and conflict detection, effect display, etc., including shelf-type element construction methods and spacecraft assembly methods based on shelf elements.

(1) Construction method of shelf elements

The shelf element construction method defines a set of geometric models that can effectively describe design elements and provides corresponding construction methods and component libraries. Usually the geometric model information of elements in shelf design is qualitative, that is, the topology, position, orientation and other relationships between functional surfaces are qualitative. At the same time, its geometric model is not only a description of the shelf design results, but more importantly Realize the division of structure and function, form a prototype design, and enable the design to be automatically transferred to the subsequent interaction process. In the design, not only geometric features should be considered, but also work characteristics, material characteristics and other characteristic elements that are important for subsequent interactions should be considered. Therefore, the shelf-type element construction combines the three-dimensional characteristics of common spacecraft platforms and payloads in the past, and creates a feature model library for some common payloads and spacecraft platforms. Considering that all models cannot be exhausted and in order to adapt to the construction needs of some new models, Some simple shape models such as spheres, cylinders, etc. have also been added, allowing users to quickly generate abstract loads, part feature models and spacecraft through interactive methods.

The results of the construction of shelf elements can be used for auxiliary analysis, simulation analysis, etc. of trial training task scenarios. Therefore, in addition to geometric topological features, each designed geometric model should also include multiple attributes such as material features. Therefore, it is necessary to conduct a detailed analysis of the characteristics of spacecraft structural components, and summarize the definitions and classifications in the current field of trial training. They can be initially divided into shape characteristics, working characteristics (coverage analysis, occlusion analysis, communication analysis), and material characteristics (rendering, Mechanical analysis, thermal analysis), etc.

a) Shape characteristics

Considering the diversity of trial training missions and spacecraft loads, the shapes, structures, functions, and assembly requirements of each load and component are greatly different, and new loads that have never been designed before will also be encountered. In the rapid design of spacecraft, the expression of loads should be as general, simple and general as possible, with a high level of abstraction. In this way, the details that do not require attention in the trial training tasks can be ignored, and the trial training personnel can focus on the most important and general common issues, and quickly configure the trial training tasks.

For spacecraft payloads and components that have been used in previous missions for a long time and whose functions and shapes have been relatively fixed, a component feature model library formed through pre-summarization and refinement is available for use, and editing functions such as three-axis scaling and rotation are provided. The feature model library not only stores the shape characteristics of the load, but also stores the material characteristics and working characteristics of the load. Commonly used loads and components like this include solar cell sail panels, lithium-ion battery boxes, star sensors, star computers, GPS receivers, nozzles, various transmitting and receiving antennas, etc.

For relatively unique and innovatively designed loads and components, since they are designed for the first time, they can only be replaced by simple geometric models, and other features can be input as required. Therefore, another way to construct shelf elements is to use some predefined simple expression shapes to represent the satellite payload, and to assist in displaying it with colors, text, parameters, etc. These simple expression shapes can be cubes, cuboids, cylinders, rods, spheres, etc., as shown in the figure below. It can be seen that the simplified model representation can not only meet the needs of new spacecraft design, but also simplify expression and improve modeling and design speed.

In addition, in order to increase the diversity of loads and components, the shelf element construction also provides solid modeling functions to obtain load expression through intersection, union, and difference operations. However, in actual spacecraft structural design, in order to improve communication efficiency and increase design speed, it is still advocated to use simple and general expressions as much as possible. Improve design efficiency on the basis of satisfying design expression.

b) Job characteristics

The spacecraft payload has working characteristics of a specific shape. For example, the optical camera may work in a linear scanning manner or may detect in a pyramidal field of view, while the working range of the communication equipment may be a conical field of view. The working characteristics of the load can be defined as: the body surrounded by a cone with the effective load as the center of the sphere and the effective detection distance as the radius. Several possible working characteristics are shown in Figure 3(a)-Figure 3(c), where Figure 3(a) is a schematic diagram of the linear scanning field of view, Figure 3(b) is a schematic diagram of the pyramid field of view, and Figure 3(c) is a cone Field of view diagram:

The working characteristic of linear scanning means that the image acquired by the sensor at a certain moment is a line. The direction of the line array is perpendicular to the navigation direction. One image is composed of several images, so it is also called pushbroom scanning imaging. The alignment of the pyramid's working characteristics is a quadrilateral, a typical representative of which is the Dark Matter Particle Detection Satellite. The working characteristic of a cone is that the collimator of the viewing cone is an ellipse, such as the X-ray telescope spectrometer and Lyman alpha coronagraph that are often used in solar physics.

The rack-type element construction not only defines the shape of the load, but also adds a working feature to the load as needed to assist in the design of the track and attitude. In addition, working characteristics can also be used for simple analysis, for example, it can be determined whether there are other loads or components that interfere with the field of view of the optical camera or the communication of the antenna.

c)Material, quality and other characteristics

The construction of shelf elements also provides a parametric editing method to input loads and material characteristics, mass characteristics of components, etc., and combines them with shape characteristics. Material characteristics can be used for simulation analysis or effect display, and can be exported to files to connect with other professional design software. The mass characteristics can be used to estimate the mass of the entire star to evaluate whether the design meets the mass constraints.

A feature model library is constructed through pre-refined typical component models or simple definition models of designs, and the shelf-type element organization diagram organized according to the tree structure is shown in Figure 4.

(2) Component-based spacecraft assembly method

The component-based spacecraft assembly method adopts a bottom-up structural design model, which is similar to the production process of a factory. The three-dimensional design of the components is first carried out, and then the components are assembled step by step to complete the assembly of the entire structure. The interactive assembly interface is shown in Figure 5, and the process is as follows:

a) First establish a blank design scene.

b) Select the platform type from the component column on the left, such as rod structure, plate structure, central load-bearing tube structure, shell structure, etc., and adjust the size of each part. As shown in Figure 6, it is a schematic diagram of a platform component;

c) Select the internal load component from the left component column and set the size, weight and other parameters interactively.

d) Install the load inside the platform, perform simple collision detection and adsorption, and set the installation posture of the load to determine the size and direction of the load field of view.

e) Install the external load of the platform, adjust the size, weight, material and other characteristic parameters, set the size and direction of the detection field of view, select the turntable type, install and set the movement mode.

f) Select the communication antenna type, installation method and installation location.

g) Select the solar panel type, set the installation position and deployment method.

h) Install other types of components.

i) Complete the structural design and upload the design results. The above steps can be repeated if necessary.

3. Feature-based rapid design technology of mission trajectory

The traditional orbit design process is: first know the goal, and then design the orbit according to the mission objectives. After completing the orbit design, see whether it can meet the requirements of the goal; if not, improve the design until the requirements are met. This process is repeated many times and the design process is complex. It is difficult to meet the demand for fast and convenient orbit design in space trial training missions.

Feature-based mission orbit rapid design technology is based on space trial mission orbit requirements. The design process and result feedback display process need to be real-time. That is, when the user design is completed, the orbit data and trajectory preview will also change accordingly. , which places higher requirements on the efficiency and real-time performance of the orbit calculation model. Considering the unpredictable characteristics of orbit design and calculation complexity in actual missions, the orbit calculation model is designed as a multi-precision multi-level loop recursion working method. That is, fitting or approximating orbit data is used in real-time response to operational changes in orbit design. When operations become less frequent and the design becomes stable, the orbit dynamics model is continuously called for recursive and accurate calculations until the accuracy meets the set error requirements. .

The feature-based task track rapid design technology is realized by the user directly operating the track on the screen. After the user changes the track on the screen, the changed track parameters are quickly given in the background. Compared with traditional track design, this graphical interactive method is intuitive, convenient and efficient. Graphical interactive track design is carried out in the following two steps.

First, a three-dimensional virtual space and celestial bodies are established to provide a reference system for the orbit. User operations on the orbit are described in this reference space. The reference space uses the J2000 coordinate system as the reference coordinate system, and the reference coordinate system commonly used in conventional satellite design is pre-established in the system. Users only need to click to obtain the corresponding coordinate system from the system. At the same time, users can also create their own coordinate system based on a specific method. The system will maintain the conversion relationship between the user coordinate system and commonly used coordinate systems. Then, the celestial bodies in the solar system are established in the created virtual space. The positions and speeds of the celestial bodies need to be supported by accurate celestial ephemerides. In addition, the rotation of celestial bodies also needs to be accurately established, and the celestial bodies also need to be divided into longitude and latitude. The ephemeris of celestial bodies can be achieved using DE405 or DE435 ephemeris.

Secondly, quickly establish or adjust the mission trajectory through orbit feature points. First, you need to create a default track to provide users with operating objects. Users can create default tracks by drawing directly on the screen, selecting from the background database, and inputting parameters. After the default track is established, the track feature points reflecting the current track metric information will be displayed in an eye-catching manner. Users can adjust the track by adjusting a series of feature points on the track. As shown in the figure, the user can click on any of the feature points and drag them to change the shape and orientation of the track until the track can cover the task target that the user needs to complete. The system uses the relative relationship between the orbital feature points, the central celestial body and the virtual three-dimensional space to extract the input information required for orbital root number calculation and complete the rapid calculation of orbital root number. When the user changes the position of a feature point, other feature points will change accordingly so that the changing track conforms to the real track characteristics. After the user completes the rapid orbit design, the system should convert these visual design results into satellite orbit elements and store them. The specific calculation process is described below.

As shown in Figure 7, it is a quick construction diagram of an orbit based on feature points; when the user completes the drawing of an orbit on the screen, the system will quickly calculate the coordinate values of the four reference points. The reference system of this coordinate value is J2000 inertia. Coordinate system (if the center is the earth, it is the Earth's J2000 coordinate system, if the center is other celestial bodies, it is the inertial coordinate system of the corresponding celestial body). Let the coordinates of the four reference points be

AP _A =(x _A y _A z _A )

BP _B =(x _B y _B z _B )

CP _C =(x _A y _A z _A )

DP _D =(x _A y _A z _A )

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

The far and near points of the target orbit are respectively

r _a =d _B ,r _p =d _A

The semi-major axis of the target orbit is

When the orbit is a circular orbit, the orbit radius is equal to the semi-major axis of the orbit, that is

R=r _a =r _p

In the formula, R is the radius of the circular orbit.

The eccentricity of the target orbit is

When the orbit is a circular orbit, the eccentricity is zero, that is, e=0.

The calculation of the orbital inclination angle of the target orbit is relatively cumbersome. First, calculate the value of the normal vector of the orbit in the inertial coordinate system, that is

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 orbit normal vector, the orbit inclination angle i can be calculated with the following formula

In the formula, ||H|| represents the module of the orbit normal vector H. This formula can also be used to calculate the inclination of the orbit when the orbit is a circular orbit.

To calculate the right ascension of the ascending node, you first need to find the intersection of the orbital plane and the equatorial plane. There are two such intersection points, namely the ascending node and the descending node. The intersection points as ascending and descending intersections need to be specified by the user, that is, the orbit running direction the user wants. According to the user's requirements, the ascending node is selected, assuming it to be point D. Find the coordinate point with zero Z direction near point D, that is, P _a (x _a , y _a , z _a = 0) (see the figure). This point is the ascending node. The angle between the line connecting the ascending node and the coordinate center and the x-axis of the inertial coordinate system is the right ascension of the ascending node, and its calculation process is:

In the formula, ||P _a || represents the module of vector P _a . The above formula also applies to calculating the right ascension of the ascending node of a circular orbit.

The argument of perigee is the angle corresponding to the arc segment from perigee to ascending node. Among the four reference points, point A is at the perigee, and the argument of the perigee can be calculated using the following formula.

In the formula, ||·|| represents the module of the vector. When the orbit is a circular orbit, there is no distinction between far and perigee, so there is no perigee argument root.

The five parameters of the six orbital numbers are calculated above. Through these five parameters, the position of the target orbit in the inertial space can be completely determined. The sixth parameter among the six numbers is the true periapsis angle, which represents the relative position of the satellite in the orbit. The true periapsis angle f of the satellite can be determined by the user dragging the satellite's position in the orbit.

After completing the fast orbit root number calculation, if the user wants to obtain the accurate orbit root number, it is necessary to calculate the orbit data in the Cartesian coordinate system. At this time, it is necessary to convert the orbital radicals into orbital parameters in the Cartesian coordinate system, and then use the orbital parameters in the Cartesian coordinates to perform recursive calculations to obtain a more accurate orbit. Calculate according to the following conversion process:

a. Calculate the current distance from the center of the earth

b. Calculate the argument of the current satellite

u=ω+f

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

d. Figure 8 shows the relationship between satellite positions on the celestial sphere. Among them, point s is the projection of the satellite on the celestial sphere. It can be obtained from the spherical trigonometric relationship

e. Calculate the current satellite rate v

f. Calculate the components of velocity

The satellite velocity direction is in the orbital plane, and it is assumed to point to the s′ point in the figure. The angle between s′ and s is

|r×v|=h

Right now

It can be judged from the tangent direction of the orbital ellipse that when f is in the I and II quadrants, In the I quadrant; when f is in the III and IV quadrants,/> In Quadrant II.

make Using the spherical trigonometric formula we can get

After completing the calculation of orbit parameters in Cartesian coordinates, the orbit parameters can be used to calculate orbit data, that is, orbit recursion. The recursion formula is as follows.

In the formula, x, y, z are satellite coordinates; is the distance from the satellite to the center of the earth; μ is the earth’s gravitational constant.

Technical effects of the system of the present invention:

1) Rapid generation of celestial bodies and surfaces

The rapid generation of celestial bodies and surfaces includes the rapid generation of skylight background, solar system celestial bodies, celestial body surface environment and other elements.

The rapid generation of skylight background realizes the generation and drawing of constellations, galaxies, nebulae, etc. based on the data of public star catalogs such as Ibagu star catalog and SAO catalog. Figure 9 is the rendering of skylight background generation.

The rapid generation of solar system celestial bodies drives the movement of solar system planets and satellites based on real ephemeris data to form a solar system celestial body movement scene. Figure 10 is a rendering of solar system celestial body generation.

The surface environment of celestial bodies is quickly generated, such as the earth's surface environment. Its topography and landforms are implemented based on multi-resolution geographical data using texture mapping. The atmospheric effects are generated and rendered based on a single scattering model. Figure 11 Multi-resolution generation rendering of the earth.

2) Rapid generation of space environment

The rapid generation of space environment includes the rapid generation of environmental factors that affect the operation of spacecraft, such as the earth's magnetic field, radiation belts, and solar wind.

The earth's magnetic field is based on the magnetic field line tracking method, and the magnetic field intensity is calculated using the international reference geomagnetic field or the T96 magnetospheric magnetic field model according to the location. Figure 12 is a rendering of the earth's magnetic field.

The Earth's radiation belts are based on the electron AE8 and proton AP8 radiation belt models, and are characterized by the outermost fusion cross-section method to form a visualization effect. Figure 13 is a visualization effect diagram of the cross-section based on radiation belt data.

The solar wind uses magnetic field line tracking to form the solar wind interplanetary magnetic field effect based on data sampling. Figure 14 shows the solar wind interplanetary effect.

3) Rapid interactive generation and design of shelf-type spacecraft structures

Extract common payloads and spacecraft platforms in the past or build a simple shape model to create a feature model library to form a shelf element. The target spacecraft can be quickly constructed through drag-and-drop click, zoom and other operations. Figure 15 shows the rapid design of the shelf spacecraft structure. Renderings.

4) Rapid interactive generation and design of task tracks based on features

Use the drag-and-drop orbit interactive design method to change the number of orbit elements to quickly form a new orbit: set the characteristic points according to the six elements of the elliptical orbit, and change these feature points by dragging the mouse to realize the interactive design of the orbit. At the same time, you can use the six elements of the elliptical orbit to Change the relevant values directly in the number setting panel. Figure 16 is a quick design rendering of the task track based on features.

Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not limiting. Although the present invention has been described in detail with reference to the embodiments, those of ordinary skill in the art will understand that modifications or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and they shall all be covered by the scope of the present invention. within the scope of the claims.

Claims (10)

1. A large-scale space trial training task scene rapid generation system, characterized in that the system includes: The task training environment generation module is used to generate the task training environment through spatial environment data or computing models; The spacecraft generation module is used to build shelf-type elements, and use human-computer interaction to combine and generate different spacecrafts based on the shelf-type elements; A mission trajectory generation module for generating mission trajectories in a graphical and interactive manner; and The trial training mission scenario generation module is used to integrate the mission training environment, spacecraft and mission orbit to form a trial training mission scenario. 2. The large-scale space trial training mission scene rapid generation system according to claim 1, characterized in that, in the mission training environment generation module, generating the mission training environment includes: generating the earth's magnetic field, generating the earth's radiation belt and generating the solar wind. ; Among them, the earth's magnetic field includes internal source field and external source field; The generation of the earth's magnetic field includes: using the international standard "International Reference Geomagnetic Field" in geophysics to calculate the internal source field, using the T96 magnetospheric magnetic field model to calculate the external source field; and using magnetic field lines to characterize the earth's magnetic field; The generation of the earth's radiation belt includes: using the electron AE8 and proton AP8 modes to calculate the earth's radiation belt, and using the outermost fusion cross-section method to calculate the omnidirectional direction of protons and electrons with different energies in the radiation belt in space. Visual representation of the distribution of integrated flux to characterize the Earth's radiation belts; The generation of solar wind includes: simulating the density, temperature, velocity and magnetic field distribution of plasma in the solar wind within a 1AU spatial range based on existing observational data, wherein density and temperature are described by only one data item; velocity and magnetic field strength need to be determined by the components in the three coordinate axis directions; and a data item is converted into color based on the color table to characterize the density or temperature, using the magnetic field line generation method in the earth's magnetic field rapid generation method, through the solar wind data Medium interpolation generates characterization effects on velocity and magnetic field strength. 3. The large-scale space trial training task scene rapid generation system according to claim 2, characterized in that the calculation formulas of the north component X, the east component Y and the vertical downward component Z of the internal source field are respectively: : Among them, (r, θ, λ) is the geocentric coordinate, r is the geocentric distance, θ is the geographical colatitude; λ is the geographical longitude, a is the radius of the earth, and/> is the Gaussian coefficient of a certain order N at time t,/> is the m-order Schmidt quasi-normalized Legendre function of order n; The T96 magnetospheric magnetic field model uses solar wind pressure, DST index, interplanetary magnetic field and geomagnetic inclination to calculate the external magnetic field at a certain point in space; The use of magnetic field lines to characterize the earth's magnetic field specifically includes: determining the initial position point P1 of the magnetic field lines, advancing to P2 with a small step size T in the direction of the magnetic field according to the magnetic field strength at this point, and repeating the above process at point P2 until Reach the boundary or other termination conditions of the data field; the magnetic field strength of any point P is calculated based on its location using the international reference geomagnetic field or the T96 magnetospheric magnetic field model; When simulating the density, temperature, velocity and magnetic field distribution of solar wind plasma in space, the space solar wind data is sampled in polar coordinate space, specifically including: The reference coordinate axes of the solar ecliptic coordinate system are identified with the x-axis, y-axis and z-axis, as given by The ternary formula determines the spatial position of each sampling point. r' is the distance from the sampling point to the heliocenter of the sun. θ' is the intersection between the projection of the line connecting the sampling point and the heliocenter in the ecliptic plane and the x-axis of the heliocentric ecliptic coordinate system. angle,/> It is the angle between the line connecting the sampling point and the heliocenter and the z-axis of the heliocentric ecliptic coordinate system; the attribute domain of each sampling point includes: background field density, background field temperature, and particle density, temperature, and magnetic field intensity at a certain simulation moment and radial velocity; when sampling, the closer to the heliocenter, the higher the data sampling frequency per unit distance. 4. The large-scale space trial training mission scene rapid generation system according to claim 1, characterized in that, in the spacecraft generation module, constructing shelf elements includes: summarizing and summarizing the three-dimensional characteristics of each spacecraft platform and load. , extract the three-dimensional structure of typical components for digitization, define geometric models, establish model templates and components, and provide corresponding construction methods and component libraries; among them, When defining the geometric model, include defining the geometric topological characteristics, shape characteristics, work characteristics, material characteristics and quality characteristics of the geometric model; when defining the work characteristics, at least perform coverage analysis, occlusion analysis and communication analysis on the components; when defining the work characteristics, at least Perform rendering analysis, mechanical analysis, and thermal analysis on components. 5. The large-scale space trial training mission scene rapid generation system according to claim 1, characterized in that, in the spacecraft generation module, when different spacecrafts are generated based on the human-computer interaction method based on shelf-type elements, the following methods are used: The bottom-up structural design model first carries out the three-dimensional design of the components, and then assembles the components step by step to complete the assembly of the entire spacecraft structure, including: a) Establish a blank design scene; b) Select the type of spacecraft platform and adjust the size of each part of the spacecraft platform; c) Select the spacecraft’s internal load components and adjust parameters, including size and weight; d) Install and detect the internal load of the platform, including collision and adsorption, while setting the installation posture of the load and determining the size and direction of the load field of view; e) Install the external load of the platform, adjust the characteristic parameters, including size, weight and material, set the size and direction of the detection field of view, select the turntable type, install and set the movement mode; f) Select the communication antenna type, installation method and installation location; g) Select the solar panel type, set the installation position and deployment method; h) Complete the spacecraft structural design. 6. The large-scale space trial training mission scene rapid generation system according to claim 1, characterized in that the mission orbit generation module includes: a space generation unit, a celestial body generation unit, an orbit calculation and adjustment unit, wherein, The space generation unit is used to establish a three-dimensional virtual space and establish a reference coordinate system; The celestial body generation unit is used to establish celestial bodies in the solar system in a three-dimensional virtual space, including the position, speed and rotation of the celestial bodies, and divide the celestial bodies into longitude and latitude; The orbit calculation and adjustment unit is used to establish, adjust and generate mission orbits in a three-dimensional virtual space through orbit feature points. 7. The large-scale space trial training task scene rapid generation system according to claim 6, characterized in that, in the orbit calculation and adjustment unit, the task orbit is established, adjusted and generated in the three-dimensional virtual space through orbit feature points, include: Establish a default orbit as the operation object by directly drawing on the screen, clicking from the system background database, or inputting parameters. When drawing directly on the screen to establish the default orbit, the orbit feature points and the central celestial body, The relative relationship in the virtual three-dimensional space extracts the input information required for orbit root number calculation to complete the calculation of fast orbit root number; After the default orbit is established, the shape and orientation of the orbit are changed by adjusting a series of orbit feature points on the orbit that reflect the current orbit metric information until the orbit can cover the mission goals that the user needs to complete. The adjustment of the orbit is completed and the mission orbit is generated. 8. The large-scale space trial training task scene rapid generation system according to claim 7, characterized in that, in the process of completing the calculation of the fast orbit root number, when the orbit is an elliptical orbit, the calculated orbit root number includes: half The calculation formulas for the major axis a, eccentricity e, orbital inclination i, perigee argument ω, ascending node right ascension Ω and true periapsis angle f are: Among them, r _a and r _p represent the far and perigee radii of the target orbit respectively: r _a =d _B ,r _p =d _A ; d _j represents the distance from the reference point j to the center point; (x _j , y _j , z _j ) represents the coordinate P _j of the reference point j; In the formula, ||H|| represents the module of the orbit normal vector H; H=(h _x h _y h _z ) ^T =P _A ×P _C =P _C ×P _B =P _B ×P _D = _PD ×P _A , (h _x h _y h _z ) represents the orbit normal vector; In the formula, O is the coordinate center, P _a (x _a , y _a , z _a = 0) is the ascending node, ||OP _a || represents the module of the vector connecting the ascending node and the coordinate center; In the formula, ||·|| represents the module of the vector; The true periapsis angle f is determined by the user dragging the position of the satellite in orbit. 9. The large-scale space trial training task scene rapid generation system according to claim 8, characterized in that in the orbit calculation and adjustment unit, the task orbit is established, adjusted and generated in the three-dimensional virtual space through orbit feature points, and further includes : After completing the calculation of the fast orbit root number, convert the orbit root number into the orbit parameters in the Cartesian coordinate system, and then use the orbit parameters in the Cartesian coordinate system to perform recursive calculations to obtain a more accurate orbit. 10. The large-scale space trial training task scene rapid generation system according to claim 9, characterized in that the transformation of orbital root numbers into orbital parameters in a Cartesian coordinate system includes: a) Calculate the current geocentric distance r: b) Calculate the argument u of the current satellite: u=ω+f c) Calculate the three components x, y, z of the current satellite position: Among them, point s is the projection of the satellite on the celestial sphere, r is the geocentric distance, i is the orbital inclination, u is the argument of the current satellite, and Ω is the right ascension of the ascending node; d) Calculate the current satellite rate v: Among them, μ is the gravitational constant of the earth; e) Calculate the components of velocity in, The s′ point represents the pointing point of the satellite velocity direction in the orbital plane, and ˙ represents a derivation; the angle between s′ and s satisfies: When f is in the I and II quadrants, In the I quadrant; when f is in the III and IV quadrants,/> In Quadrant II. When performing recursive calculation using orbital parameters in Cartesian coordinates, the recursive formula is: In the formula, x, y, z are satellite coordinates, and ¨ represents the quadratic derivation; is the distance from the satellite to the center of the earth.