Space target situation display method and system

Abstract

The present application relates to a space target situation display method and system, which uses two parameters of orbit height and orbit inclination in six numbers of space target orbit to represent the deployment of space targets, and combines icon design to represent different countries and different types of space targets in the graph. On this basis, a space target parameter anomaly index is constructed and calculated, which can represent whether there is an abnormal change in the current state of the space target compared with the state at a certain time point. The size of the space target parameter anomaly index is displayed in the situation graph through the size of the icon, and then the use of space equipment is displayed.

Description

Technical Field

[0001] This invention relates to the field of space technology, and specifically to a method and system for displaying the status quo of space targets. Background Technology

[0002] Space target situational awareness plays a crucial role in modern space domain identification, mission planning, and military decision-making. Accurate and real-time understanding of space target deployment and operational information is essential for ensuring the success of space operations. However, current space target situational awareness faces numerous challenges. First, the motion characteristics of space targets differ from those of ground, sea, or air targets. Even when statically deployed in space, space targets are constantly changing positions and move along an orbit. Second, the wide spatial distribution: the distribution and activity range of space targets far exceeds that of ground targets, spanning orbital altitudes from hundreds to tens of thousands of kilometers. The scale of activity range varies greatly among different space targets, making it extremely challenging to clearly display the activities of all targets on a single situational awareness map, especially when the number of targets is very large. Third, the influence of external disturbances: the trajectory of space targets is affected by various perturbations such as the atmosphere, Earth's non-spherical gravity, solar radiation pressure, and third-body gravity. This makes identifying the cause of orbital changes difficult, and distinguishing whether orbital changes are caused by disturbances or their own maneuvers is a challenge.

[0003] Traditional methods for displaying the situation of space targets involve showing their orbits within 3D and 2D Earth maps. The well-known aerospace simulation software STK provides classic 3D and 2D fields of view to intuitively present the state of space targets in the 3D physical world and their projection onto a 2D world map. The advantage of this method is its intuitiveness and lack of information loss. However, its disadvantages include view clutter and excessive computational load when dealing with a large number of space targets. Furthermore, this method struggles to clearly represent the changes of multiple space targets over a period of time in a single situation map. Therefore, providing an intuitive and information-rich method for displaying the situation of space targets, overcoming the challenges of target motion, vast spatial range, and difficulty in distinguishing disturbances, and improving the readability of space target situation maps is a key technical problem that needs to be solved. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention proposes a method and system for displaying the situation of space targets, applicable to presenting the deployment and operational information of space equipment by both sides in space warfare. First, based on the operational patterns and orbital characteristics of space equipment, two parameters—orbital altitude and orbital inclination—are selected to characterize the deployment of space targets. This clearly displays the orbits of space targets while avoiding the influence of rapidly changing variables such as orbital apogee angle on the situation presentation, solving the problem of displaying a massive number of space targets with different orbital altitudes on a single map. Then, icons of different colors and shapes are used to represent space targets of different countries and types, showcasing the deployment and operational status of space equipment by both sides in space warfare. Finally, a space target parameter variation index is constructed to characterize its abnormal changes. This variation index considers not only multiple characteristics of the space target itself but also the variation of similar targets, thus presenting comprehensive variation information simply and intuitively while eliminating the influence of normal disturbances. This method uses a two-dimensional scatter plot to present the situation of space targets, offering simplicity, intuitiveness, and rich information.

[0005] Specifically, in a first aspect, embodiments of the present invention provide a method for displaying the situation of a spatial target, the method comprising:

[0006] S1, establish a coordinate system;

[0007] S2, construct icons of different colors and shapes, where colors represent different countries and shapes represent different spatial target types;

[0008] S3, Construct the spatial target parameter variation index;

[0009] S4, calculate the state value of the space target based on the space target parameter variation index;

[0010] S5, calculate the Z score of the variation index of similar spatial target parameters;

[0011] S6 forms a spatial target situation map based on S1-S5.

[0012] Furthermore, in S1:

[0013] Construct a coordinate system with the track inclination angle as the X-axis and the track height as the Y-axis. The X-axis ranges from 0 to 180°, and the Y-axis ranges from 100km to 50,000km.

[0014] The coordinates of the space target in the coordinate system are (i, h), where i is the orbital inclination of the space target and h is the orbital altitude of the space target above the Earth's surface.

[0015] Furthermore, in S3:

[0016] The equation for calculating the parametric variation index J is:

[0017]

[0018] Where 1≤j≤n, n is the number of characteristic parameters of the space target, Δf j w represents the change of the characteristic parameters of the j-th spatial target. j The weights of the feature parameters of the j-th spatial target;

[0019] For slow variables that remain stable over a long period, Δf j Indicates parameter f j The equation for calculating the change in the value at the time of the situation map representation relative to the value at the reference time is:

[0020] Δf j =f j (t0)-f j (t1)

[0021] Among them, f j (t) represents the value of the j-th spatial target characteristic parameter at time t, t0 represents the time represented by the situation map, and t1 represents the situation reference time;

[0022] For the fast variable mean anterior angle, Δf j The equation representing the change in the mean approach angle M at the moment of situation characterization relative to the mean approach angle calculated from the reference moment under no-maneuver conditions is as follows:

[0023]

[0024] Where a(t1) is the semi-major axis of the orbit of the space target at time t1, and μ is the Earth's gravitational constant, which is the product of the Earth's mass and the gravitational constant.

[0025] When f j When the parameter representing the angle is Δf j The value is transformed to the interval [-π, π].

[0026] Furthermore, in S4:

[0027] Calculate the orbital altitude, orbital inclination, and parameter variation index relative to a certain historical moment for all space targets at the moment represented by the situation diagram, and obtain the state value A of the space targets, expressed as:

[0028] A k ={i k ,h k J k C k ,T k}

[0029] Where 1≤k≤m, m is the number of space targets, C k The value T represents the country to which the space target belongs. k This indicates the value corresponding to the type to which the space target belongs.

[0030] Furthermore, in S5:

[0031] The formula for calculating the Z-score is:

[0032]

[0033] in, J represents k The average parametric variation index of the spatial targets in the same category, S represents J k The standard deviation of spatial targets in the same category;

[0034] When the Z score exceeds the predetermined range, it is considered that J k Characterize the anomaly of the space target; otherwise, consider J to be... k These are normal parameter changes caused by the space environment and the normal operation of the satellite. By comparing with similar space targets, we can determine whether the space target has undergone abnormal movement and eliminate gravitational perturbations or other interferences.

[0035] The parameter variation index J′ determined by the Z-score k for:

[0036]

[0037] Where V is the set threshold;

[0038] Thus, the state value A′ of the space target is obtained. k ={i k ,h k ,J′ k C k ,T k}

[0039] Secondly, embodiments of the present invention also provide a space target situation display system based on the space target situation display method described in any of the first aspects above. The system includes: a database module for storing various characteristic parameters of space targets at different times; a calculation module for calculating the space target state value at a specific time relative to a certain time based on the information provided by the database module; and a space target situation display module for drawing a space target situation map based on the rules of the space target situation display method and the value provided by the calculation module.

[0040] The space target situation display method and system of this invention utilizes a two-dimensional scatter plot incorporating icons to present the space target situation, offering advantages such as simplicity, intuitiveness, rich information, and high computational efficiency. By constructing a view with orbital inclination and altitude as coordinate axes, it simplifies the presentation while highlighting effective space target deployment information, clearly showing the orbital region where the space target is located. By designing icons of different colors and shapes to display the country and type of space targets, it comprehensively reflects the deployment status of different types of space targets in various countries. Furthermore, by constructing a space target parameter variation index that integrates changes in multiple characteristic parameters and comparing similar space targets, it comprehensively reflects anomalies such as orbital and attitude changes of space targets, while also eliminating interference from disturbances such as gravitational perturbations. This method effectively solves problems in space target situation display such as space target movement, wide spatial range, and difficulty in identifying external disturbances, making it suitable for presenting the deployment and application information of space equipment of both sides in space warfare. Attached Figure Description

[0041] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0042] Figure 1 This is a flowchart illustrating the spatial target situation display method according to an embodiment of the present invention;

[0043] Figure 2 A simplified schematic diagram of a situational awareness diagram generated according to an embodiment of the present invention. Detailed Implementation

[0044] The description of the embodiments in this specification should be taken in conjunction with the accompanying drawings, which should form part of the complete specification. In the drawings, the shape or thickness of the embodiments may be exaggerated and may be indicated in a simplified or convenient manner. Furthermore, parts of the various structures in the drawings will be described separately; it is worth noting that elements not shown in the figures or not described in words are in a form known to those skilled in the art.

[0045] The descriptions of the embodiments herein, including any references to directions and orientations, are for ease of description only and should not be construed as limiting the scope of the invention. The following description of preferred embodiments involves combinations of features, which may exist independently or in combination; the invention is not particularly limited to the preferred embodiments. The scope of the invention is defined by the claims.

[0046] The spatial target situation display method of this invention includes:

[0047] Step S1: Construct a coordinate system with the orbital inclination and orbital altitude as the X and Y axes. The X-axis is in degrees and ranges from 0 to 180°; the Y-axis is in kilometers and ranges from 100km to 50000km; the coordinates of the space target in the coordinate system are (i, h), where i is the orbital inclination of the space target and h is the orbital altitude of the space target above the Earth's surface.

[0048] When considering the overall deployment of space targets, 'i' can effectively characterize the location of the space target's orbit, while 'h' can effectively characterize the shape of the space target's orbit. Orbits are generally classified by altitude into Low Earth Orbit (LEO), Medium Earth Orbit (MEO), Geosynchronous Orbit (GSO), and High Earth Orbit (HEO), and by inclination into equatorial orbits, polar orbits, retrograde orbits, etc. Using orbital inclination and altitude, the orbital region where a space target is located can be well characterized.

[0049] In this coordinate system, several commonly used orbital regions for spacecraft can be divided. For example, the region with an orbital altitude below 2000km is the LEO region, where different orbital shells can be further distinguished according to altitude, clearly showing the shells where giant low-Earth orbit constellations are located; the region with an orbital inclination close to 90° is the region where polar orbits are located, and the sun-synchronous orbit commonly used by Earth observation satellites also exists there; the region with an orbital altitude greater than 2000km but lower than the geostationary orbit altitude is the MEO region, which is mostly used for deploying navigation satellites; the region with an orbital altitude of about 35786km is the GSO region, where the orbital inclination close to 0° is the geostationary orbit (GEO) region, and the region with a larger orbital inclination is the inclined geosynchronous orbit (IGSO) region.

[0050] Step S2: Construct icons of different colors and shapes. Colors represent different countries; for example, red represents space targets of country A, blue represents space targets of country B, and gray represents space targets of other countries. Shapes represent different types of space targets; for example, circles, squares, rhombuses, ellipses, hexagons, trapezoids, stars, and triangles represent communication satellites, navigation satellites, Earth observation satellites, manned spacecraft, space science satellites, technology demonstration satellites, rocket upper stages, and space debris, respectively.

[0051] Step S3: Construct a spatial target parameter variation index that integrates the changes of multiple characteristic parameters. The calculation equation for the parameter variation index J is:

[0052]

[0053] Where: 1≤j≤n, and n is the number of characteristic parameters of the space target. Δf j Characterizes the changes in the feature parameters of the j-th spatial target. j represents the weight of the characteristic parameters of the j-th space target. The characteristic parameters of a space target include, but are not limited to, the semi-major axis of its orbit, its eccentricity, its inclination, its secondary perigee angle, its right ascension of the ascending node, its mean perigee angle, its radar cross-section, and its optical cross-section.

[0054] For slow variables that remain stable over a long period, Δf j Indicates parameter f j The equation for calculating the change in the value at the time of the situation map representation relative to the value at the reference time is:

[0055] Δf j =f j (t0)-f j (t1)

[0056] Among them, f j (t) represents the value of the j-th spatial target characteristic parameter at time t, t0 represents the time represented by the situation map, and t1 represents the situation reference time.

[0057] For the fast variable mean anterior angle, Δf j The equation representing the change in the mean approach angle M at the moment of situation characterization relative to the mean approach angle calculated from the reference moment under no-maneuver conditions is as follows:

[0058]

[0059] Where a(t1) is the semi-major axis of the orbit of the space target at time t1, and μ is the Earth's gravitational constant, which is the product of the Earth's mass and the gravitational constant.

[0060] It is important to note that when f j When the parameter being represented is an angle, Δf needs to be... j The value is transformed to the interval [-π, π].

[0061] Step S4: Calculate the orbital altitude, orbital inclination, and parameter variation index relative to a certain historical time for all space targets at the moment represented by the situation diagram, to obtain the state value A of the space targets, expressed as:

[0062] A k ={i k ,h k J k C k ,T k}

[0063] Where: 1≤k≤m, m is the number of space targets, C kThe value T represents the country to which the space target belongs. k This indicates the value corresponding to the type to which the space target belongs.

[0064] Step S5: Calculate the Z-score of the variation index of similar spatial target parameters. The calculation formula is as follows:

[0065]

[0066] in, J represents k The average parameter variation index of the spatial targets in the same category, S, represents J. k The standard deviation of a space target within its category. Space target categories are defined based on two dimensions: orbital region and space target category, such as GEO communication satellites, MEO navigation satellites, etc.

[0067] When the Z score exceeds a certain range, it is considered that J... k Characterize the anomaly of the space target; otherwise, consider J to be... k These are normal parameter changes caused by the space environment and the normal operation of the satellite. This method, by comparing with similar space targets, determines whether the space target has experienced abnormal movement and eliminates interference such as gravitational perturbations.

[0068] Therefore, the parameter variation index J′ determined by the Z-score k for:

[0069]

[0070] Where V is the set threshold, which is usually 3.

[0071] Thus, the state value A′ of the space target is obtained. k ={i k ,h k ,J′ k C k ,T k}

[0072] Step S6: Based on the rules given above and the calculated spatial target state values, draw a spatial target situation map. k Let h be the X coordinate of the spatial target in the figure. k Let J′ be the Y-coordinate of the spatial target in the figure. k Enlarge the icon when it is not 0, C k Determine the icon color, T k Determine the shape of the icon.

[0073] Thus, this embodiment of the invention provides a method for displaying the situation of space targets, which can clearly display the deployment status of all space targets and whether any abnormalities have occurred.

[0074] Furthermore, embodiments of the present invention also relate to a system based on the aforementioned space target situation display method. The system includes a database module, a calculation module, and a space target situation display module. The database module stores various characteristic parameters of space targets at different times, including country and type, orbital parameters, target characteristics, etc.; the calculation module can calculate the space target state value at a specific time relative to a certain time based on the information provided by the database module; and the space target situation display module can draw a space target situation map based on the rules given by the space target situation display method and the values ​​provided by the calculation module.

[0075] The space target situation display method and system presented in this invention utilizes a two-dimensional scatter plot incorporating icons to present the space target situation, offering advantages such as simplicity, intuitiveness, rich information, and high computational efficiency. By constructing a view with orbital inclination and altitude as coordinate axes, it simplifies the format while highlighting effective space target deployment information, clearly showing the orbital region where the space target is located. By designing icons of different colors and shapes to display the country and type of space targets, it comprehensively reflects the deployment status of different types of space targets in various countries. Furthermore, by constructing a space target parameter variation index that integrates changes in multiple characteristic parameters and comparing similar space targets, it comprehensively reflects anomalies such as orbital and attitude changes of space targets, while eliminating interference from disturbances such as gravitational perturbations. This method effectively solves the problems of space target movement, wide spatial range, and difficulty in identifying external disturbances in space target situation display, and is suitable for presenting the deployment and application information of space equipment of both sides in space warfare.

[0076] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for displaying the situation of spatial targets, characterized in that, The method includes: S1, establish a coordinate system; S2, construct icons of different colors and shapes, where colors represent different countries and shapes represent different spatial target types; S3, Construct the spatial target parameter variation index; S4, calculate the state value of the space target based on the space target parameter variation index; S5, Calculate the variation index of similar spatial target parameters. Fraction; S6, based on S1-S5, forms a spatial target situation map; In S1: Construct a coordinate system with the track inclination angle as the X-axis and the track height as the Y-axis. The X-axis ranges from 0 to 180°, and the Y-axis ranges from 100km to 50,000km. The coordinates of the space target in the coordinate system are ( (h), where, Let θ be the orbital inclination of the space target, and h be the orbital altitude of the space target above the Earth's surface. In S3: Parameter variation index The calculation equation is as follows: in, , The number of feature parameters of the space target. Characterizing the first The changes in the feature parameters of each spatial target For the first Weights of spatial target feature parameters; For slow variables that remain stable over a long period of time Indicates parameters The equation for calculating the change in the value at the time of the situation map representation relative to the value at the reference time is: in, express Time of the first The values ​​of the feature parameters of a spatial target Indicates the moment represented by the situation diagram. Indicates the situation reference time; For fast variable mean anterior angle The situation diagram represents the angle of approach at any given moment. The value of is relative to the value of the mean approach angle at the time of the situation map characterization, calculated from the reference time under no-maneuver conditions. The calculation equation is: in, for The semi-major axis of the orbit of the spatial target at any given time. is the Earth's gravitational constant, which is the product of the Earth's mass and the gravitational constant. when When the parameter being represented is an angle, Value conversion to Within the range.

2. The spatial target situation display method according to claim 1, characterized in that, In S4: Calculate the orbital altitude, orbital inclination, and parameter variation index relative to a certain historical moment for all space targets at the moment represented by the situation diagram to obtain the state values ​​of the space targets. , is represented as: in, , The number of space targets. This indicates the value corresponding to the country to which the space target belongs. This indicates the value corresponding to the type of the space target.

3. The spatial target situation display method according to claim 1, characterized in that, In S5: The formula for calculating the Z-score is: in, express The average parametric variation index of the spatial targets in the category, S represents The standard deviation of spatial targets in the same category; when When the score exceeds the predetermined range, it is considered... Characterize the anomalies of space targets; otherwise, consider... These are normal parameter changes caused by the space environment and the normal operation of the satellite. By comparing with similar space targets, we can determine whether the space target has undergone abnormal movement and eliminate gravitational perturbations or other interferences. go through The parameter variation index for score judgment for: in, The set threshold; Thus, the state values ​​of the space target are obtained. .

4. A space target situation display system based on the space target situation display method according to any one of claims 1-3, characterized in that, The system includes: The database module is used to store various characteristic parameters of spatial targets at different times; The calculation module calculates the spatial target state value at a specific time relative to a certain time based on the information provided by the database module; The space target situation display module draws a space target situation map based on the rules of the space target situation display method and the values ​​provided by the calculation module.

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