Method for collision early warning detection of giant constellation, electronic device and storage medium

Abstract

The present application relates to a kind of giant constellation collision warning detection method, electronic equipment and storage medium, step S1, according to the design of protected giant constellation system, construct collision risk set;According to the design of constellation system and collision risk set, determine the intersection point that can occur collision, intersection point time;Utilize the first star-ground distance H1 of risk source satellite / debris of intersection point time, the second star-ground distance H2 of satellite of protected giant constellation, judge whether there is collision risk;Two steps described above are executed using parallel computing strategy, complete the collision risk judgment of all risk source satellite / debris in collision risk set and satellite of protected giant constellation system.The present application effectively improves the timeliness of the collision possibility detection between giant constellation and space debris, improves the collision warning detection efficiency of future giant constellation, efficiently supports satellite to carry out maneuvering adjustment, to implement collision avoidance.

Description

Technical Field

[0001] This invention relates to the field of spacecraft collision protection, specifically to a collision early warning detection method, electronic equipment, and storage medium for a giant constellation. Background Technology

[0002] With the increasing frequency of human space activities, space debris and space junk have become a widespread concern for countries around the world. Especially in recent years, the number of mega-constellations under construction or planned globally has increased, and the vast majority of these mega-constellations and space debris are concentrated in the Low Earth Orbit (LEO) region. This increases the likelihood of collisions between satellites and space debris, and the resulting fragmentation of satellites or debris will generate even more space debris. Therefore, collision detection between mega-constellations and space debris is a problem that cannot be ignored.

[0003] The current collision detection mechanism uses a constellation-debris approximation calculation method. This involves real-time prediction of the position and velocity of each satellite within the constellation, followed by real-time prediction of the position and velocity of each debris. Then, within the collision prediction period, the spatial distance between each pair of satellites and debris is calculated. If the distance is below a set collision threshold, a collision is considered to exist; otherwise, no collision is possible. CelesTrak's daily proximity reports also use this method to filter collision pairs.

[0004] Low Earth orbit (LEO) mega-constellations range in size from hundreds to thousands or even tens of thousands of objects. Directly applying the common brute-force approach to select collision pairs requires a large number of servers for parallel computation to meet the collision selection and calculation requirements within the predicted timeframe. This limits the research, simulation, demonstration, and widespread implementation of LEO mega-constellations. Therefore, under limited resource conditions, LEO mega-constellations may encounter other constellations or space debris on their orbital paths. Predicting such collision risks necessitates an efficient method for selecting space object collisions. Summary of the Invention

[0005] In view of the above-mentioned technical problems, based on a thorough analysis of the orbital characteristics of constellation satellites, this invention proposes a collision warning and detection method, electronic equipment, and storage medium for mega-constellations. This method can greatly improve the efficiency of collision warning and detection for future mega-constellations and efficiently support satellites in making maneuvering adjustments to implement collision avoidance.

[0006] The technical solution for achieving the objective of this invention is: a collision warning detection method for giant constellations, comprising the following steps:

[0007] Step S1: Construct a collision risk set based on the design of the protected mega-constellation system;

[0008] Step S2: Based on the constellation system design and collision risk set, determine the intersection points and times of potential collisions;

[0009] Step S3: Using the first satellite-to-ground distance H1 of the risk source satellite / debris at the intersection point and the second satellite-to-ground distance H2 of the protected mega-constellation satellites, determine whether there is a collision risk;

[0010] Step S4: Execute steps S2 and S3 using a parallel computing strategy to complete the collision risk assessment of all risk source satellites / debris and satellites of protected mega-constellation systems within the collision risk set.

[0011] According to one aspect of the invention, in step S1, before constructing the collision risk set, the method further includes:

[0012] Step S101: Determine the number of orbital height layers of the constellation system based on the design parameters of the protected mega-constellation;

[0013] Step S102: Calculate the perigee and apogee of each sub-layer based on the orbital altitude and eccentricity of the giant constellation sub-layers;

[0014] Step S103: Determine the height of the upper and lower bands of the orbital zone in which the constellation system is located.

[0015] According to one aspect of the present invention, in step S1, constructing a collision risk set specifically includes:

[0016] Step S104: Calculate the perigee and apogee altitudes of the satellite / debris by loading on-orbit satellite / debris ephemeris data;

[0017] Step S105: Identify satellites / debris with collision penetration zones in the protected constellation orbital zone, and construct a collision risk set for satellites / debris with collision penetration zones.

[0018] According to one aspect of the invention, in step S105, identifying the satellite / debris having a collision-piercing region with the protected constellation orbital zone specifically includes:

[0019] If the apogee altitude of a satellite / debris is greater than the upper edge of the protected constellation's orbital band, and the perigee altitude is less than the upper edge, then there is a puncture zone between the satellite / debris and the protected constellation's orbital band.

[0020] If the apogee altitude of a satellite / debris is greater than the lower edge of the protected constellation's orbital band, and the perigee altitude is less than the lower edge, then there is a puncture zone between the satellite / debris and the protected constellation's orbital band.

[0021] According to one aspect of the invention, before performing step S2, the method further includes:

[0022] The satellites of the protected mega-constellation system are reduced in dimensionality and classified according to their orbital planes;

[0023] The satellites / debris in the collision risk set are reduced in dimension and classified according to their orbital planes;

[0024] The satellites of the classified protected mega-constellation system are combined into orbital rings according to their orbital planes and the orbital planes of the classified collision risk sets of satellites / debris.

[0025] According to one aspect of the present invention, step S2 specifically includes:

[0026] Step S201: Calculate the perigee and apogee altitudes of the satellite / debris to identify the satellite / debris that has a collision puncture zone with the protected constellation orbital zone;

[0027] Step S202: Determine the intersection points of each orbital plane or extended orbital plane of the protected constellation with each orbital ring in the collision risk set;

[0028] Step S203: Based on the Keplerian laws and intersection points of satellite operation, determine the discrete time of the intersection point.

[0029] According to one aspect of the present invention, step S3 specifically includes:

[0030] Step S301: Within an orbital loop, calculate the first satellite-to-ground distance H1 between a risk source satellite / debris at the intersection point when it moves to the intersection point position based on ephemeris data;

[0031] Step S302: Within the same orbital loop, select any protected satellite and calculate the distance H2 between the satellite and the ground when the protected satellite moves to the corresponding intersection point position based on the ephemeris data;

[0032] Step S303: Determine whether |H1-H2| is greater than the collision detection threshold. If yes, it is considered that there is no collision risk. If no, proceed to step S304.

[0033] Step S304: Using the discrete time of the intersection point, calculate the position coordinates of the risk source at the corresponding time, as well as the position coordinates of each satellite on the orbital plane;

[0034] Step S305: Calculate the spatial distance between the risk source and each satellite, and determine whether the spatial distance is less than the collision detection threshold. If so, the risk source is an object with collision risk.

[0035] According to one aspect of the invention, step S3 further includes:

[0036] Step S306: Filter and record objects with collision risk, and calculate the collision probability, collision approach time, and collision approach distance.

[0037] According to one aspect of the present invention, an electronic device is provided, comprising: one or more processors, one or more memories, and one or more computer programs; wherein the processor is connected to the memory, and the one or more computer programs are stored in the memory; when the electronic device is running, the processor executes the one or more computer programs stored in the memory to cause the electronic device to perform a collision warning detection method for a giant constellation as described in any of the above technical solutions.

[0038] According to one aspect of the present invention, a computer-readable storage medium is provided for storing computer instructions, which, when executed by a processor, implement a collision warning detection method for a giant constellation as described in any of the above technical solutions.

[0039] According to the concept of this invention, a collision early warning detection method, electronic equipment, and computer program for mega-constellations are proposed. Based on the design of the protected mega-constellation system, a collision risk set is constructed. Satellites / debris in the collision risk set are paired with the protected mega-constellation system to form collision pairs. At the intersection point and time of the potential collision, the first satellite-to-ground distance H1 of the risk source satellite / debris at the intersection point and the second satellite-to-ground distance H2 of the protected mega-constellation satellites at the intersection point are used to judge the collision risk and complete the risk judgment for all collision pairs. This effectively improves the timeliness of collision probability detection between mega-constellations and space debris, provides effective collision early warning detection for subsequent collision probability calculation and collision risk assessment, and greatly improves the efficiency of future collision early warning detection for mega-constellations, efficiently supporting satellite maneuvering adjustments to implement collision avoidance. Attached Figure Description

[0040] Figure 1 The schematic diagram illustrates a process flow of a collision warning detection method for giant constellations according to an embodiment of the present invention.

[0041] Figure 2 This illustration shows a protected mega-constellation orbital zone division according to one embodiment of the present invention.

[0042] Figure 3 This illustration shows a potential collision risk area delineation according to one embodiment of the present invention.

[0043] Figure 4 A schematic diagram illustrating the track loop to be calculated, showing the presence of a puncture area according to one embodiment of the present invention;

[0044] Figure 5 This diagram illustrates the spatial location of the intersection point of the track loop according to one embodiment of the present invention. Detailed Implementation

[0045] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the accompanying drawings used in the embodiments will be briefly described below. Obviously, the drawings described below are merely some embodiments of the present invention, and those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0046] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. The embodiments cannot be described in detail here, but the embodiments of the present invention are not limited to the following embodiments.

[0047] like Figures 1 to 5 As shown, a collision warning detection method for giant constellations according to the present invention includes the following steps:

[0048] Step S1: Construct a collision risk set based on the design of the protected mega-constellation system;

[0049] Step S2: Based on the constellation system design and collision risk set, determine the intersection points and times of potential collisions;

[0050] Step S3: Using the first satellite-to-ground distance H1 of the risk source satellite / debris at the intersection point and the second satellite-to-ground distance H2 of the protected mega-constellation satellites, determine whether there is a collision risk;

[0051] Step S4: Execute steps S2 and S3 using a parallel computing strategy to complete the collision risk assessment of all risk source satellites / debris and satellites of protected mega-constellation systems within the collision risk set.

[0052] In this embodiment, a collision risk set is constructed based on the design of the protected mega-constellation system. Satellites / debris in the collision risk set are paired with the protected mega-constellation system to form collision pairs. At the intersection point and time of the potential collision, the first satellite-to-ground distance H1 of the risk source satellite / debris at the intersection point and the second satellite-to-ground distance H2 of the protected mega-constellation satellites are used to assess the collision risk. Risk assessments are completed for all collision pairs. An algorithm for detecting and processing the orbital loop intersections of the constellation and debris / satellites provides a collision pair screening mechanism for risk detection of satellites and debris in space. This effectively improves the timeliness of collision probability detection between the mega-constellation and space debris, providing effective collision warning detection for subsequent collision probability calculations and collision risk assessments. Simultaneously, it greatly improves the efficiency of future collision warning detection for mega-constellations, efficiently supporting satellite maneuvers to implement collision avoidance.

[0053] like Figure 2 and Figure 4 As shown, in one embodiment of the present invention, preferably, in step S1, before constructing the collision risk set, the following is further included:

[0054] Step S101: Determine the number of orbital height layers of the constellation system based on the design parameters of the protected mega-constellation;

[0055] Step S102: Calculate the perigee and apogee of each sub-layer based on the orbital altitude and eccentricity of the giant constellation sub-layers;

[0056] Step S103: Determine the height of the upper and lower bands of the orbital zone in which the constellation system is located.

[0057] In this embodiment, before constructing the collision risk set, it is necessary to first determine the orbital zone of the protected mega-constellation. Based on the design parameters of the protected mega-constellation, the upper and lower edge zone heights of the orbital zone where the constellation system is located are calculated, thereby initially identifying satellites / debris that pose a collision risk to the constellation system and completing the initial screening of satellites / debris.

[0058] like Figure 3 As shown, in one embodiment of the present invention, preferably, in step S1, constructing a collision risk set specifically includes:

[0059] Step S104: Calculate the perigee and apogee altitudes of the satellite / debris by loading on-orbit satellite / debris ephemeris data;

[0060] Step S105: Identify satellites / debris with collision penetration zones in the protected constellation orbital zone, and construct a collision risk set for satellites / debris with collision penetration zones.

[0061] In this embodiment, satellites / debris with collision penetration zones in the orbital zone of the protected constellation are considered targets that pose a collision risk with the satellites of the protected constellation. These targets are grouped together to form a collision risk set. Each entity in the collision risk set has its own orbit and can be regarded as an independent orbital ring.

[0062] In one embodiment of the present invention, preferably, in step S105, determining the satellite / debris having a collision-piercing region with the protected constellation orbital zone specifically includes:

[0063] If the apogee altitude of a satellite / debris is greater than the upper edge of the protected constellation's orbital band, and the perigee altitude is less than the upper edge, then there is a puncture zone between the satellite / debris and the protected constellation's orbital band.

[0064] If the apogee altitude of a satellite / debris is greater than the lower edge of the protected constellation's orbital band, and the perigee altitude is less than the lower edge, then there is a puncture zone between the satellite / debris and the protected constellation's orbital band.

[0065] In this embodiment, if the apogee altitude of the satellite / debris is greater than the upper edge of the protected constellation orbital zone and the perigee altitude is less than the upper edge, or if the apogee altitude of the satellite / debris is greater than the lower edge of the protected constellation orbital zone and the perigee altitude is less than the lower edge, it can be considered that the orbital zone of the satellite / debris intersects with the orbital zone of the protected constellation, i.e., there is a puncture zone.

[0066] In one embodiment of the present invention, preferably, before performing step S2, the method further includes:

[0067] The satellites of the protected mega-constellation system are reduced in dimensionality and classified according to their orbital planes;

[0068] The satellites / debris in the collision risk set are reduced in dimension and classified according to their orbital planes;

[0069] The satellites of the classified protected mega-constellation system are combined into orbital rings according to their orbital planes and the orbital planes of the classified collision risk sets of satellites / debris.

[0070] In this embodiment, a mega-constellation system contains multiple satellites, and satellites may have identical orbits. Therefore, two or more satellites in the same orbital band are matched according to an orbital band. Similarly, two or more satellites / debris in the same collision risk set have the same orbital band. After classification and dimensionality reduction, the orbital bands of the collision risk set are matched in pairs with the orbital bands in the mega-constellation system to form orbital loops, which effectively reduces the amount of data, speeds up the operation, and ensures the efficiency of the operation.

[0071] In one embodiment of the present invention, preferably, step S2 specifically includes:

[0072] Step S201: Calculate the perigee and apogee altitudes of the satellite / debris to identify the satellite / debris that has a collision puncture zone with the protected constellation orbital zone;

[0073] Step S202: Determine the intersection points of each orbital plane or extended orbital plane of the protected constellation with each orbital ring in the collision risk set;

[0074] Step S203: Based on the Keplerian laws and intersection points of satellite operation, determine the discrete time of the intersection point.

[0075] In this embodiment, since the risk source satellite / debris moves periodically along the orbital ring, collision detection is mainly performed near these discrete and periodic time points. By calculating the perigee and apogee altitudes of the satellite / debris, the satellite / debris with the collision puncture zone of the protected constellation orbital zone is identified, the intersection point of the orbital ring is determined, and the discrete time of the intersection point is determined based on the positions of the satellites of the protected constellation and the intersection point.

[0076] like Figure 5 As shown, in one embodiment of the present invention, preferably, step S3 specifically includes:

[0077] Step S301: Within an orbital loop, calculate the first satellite-to-ground distance H1 between a risk source satellite / debris at the intersection point when it moves to the intersection point position based on ephemeris data;

[0078] Step S302: Within the same orbital loop, select any protected satellite and calculate the distance H2 between the satellite and the ground when the protected satellite moves to the corresponding intersection point position based on the ephemeris data;

[0079] Step S303: Determine whether |H1-H2| is greater than the collision detection threshold. If yes, it is considered that there is no collision risk. If no, proceed to step S304.

[0080] Step S304: Using the discrete time of the intersection point, calculate the position coordinates of the risk source at the corresponding time, as well as the position coordinates of each satellite on the orbital plane;

[0081] Step S305: Calculate the spatial distance between the risk source and each satellite, and determine whether the spatial distance is less than the collision detection threshold. If so, the risk source is an object with collision risk.

[0082] In one embodiment of the present invention, preferably, step S3 further includes:

[0083] Step S306: Filter and record objects with collision risk, and calculate the collision probability, collision approach time, and collision approach distance.

[0084] In step S4, a parallel computing strategy is adopted to perform collision risk detection and assessment calculations on each orbital ring corresponding to the collision risk set and each orbital plane satellite in the protected constellation, until the collision detection calculations of all orbital rings during the assessment period are completed, thereby completing the overall collision warning detection.

[0085] According to one aspect of the present invention, an electronic device is provided, comprising: one or more processors, one or more memories, and one or more computer programs; wherein the processor is connected to the memory, and the one or more computer programs are stored in the memory; when the electronic device is running, the processor executes the one or more computer programs stored in the memory to cause the electronic device to perform a collision warning detection method for a giant constellation as described in any of the above technical solutions.

[0086] According to one aspect of the present invention, a computer-readable storage medium is provided for storing computer instructions, which, when executed by a processor, implement a collision warning detection method for a giant constellation as described in any of the above technical solutions.

[0087] In summary, this invention proposes a collision warning detection method, electronic device, and storage medium for mega-constellations. Step S1 involves constructing a collision risk set based on the design of the protected mega-constellation system; determining potential collision intersection points and their times based on the constellation system design and the collision risk set; using the first satellite-to-ground distance H1 of the risk source satellite / debris at the intersection point and the second satellite-to-ground distance H2 of the protected mega-constellation satellites at the intersection point to determine if a collision risk exists; and executing steps S2 and S3 using a parallel computing strategy to complete the collision risk assessment of all risk source satellites / debris and satellites within the collision risk set. This invention, through an algorithm for detecting and processing the orbital intersection points of constellations and debris / satellites, provides a collision pair screening mechanism for risk detection of satellites and debris in space, effectively improving the timeliness of collision probability detection between mega-constellations and space debris. This provides effective collision warning detection for subsequent collision probability calculations and collision risk assessments, while significantly improving the efficiency of future collision warning detection for mega-constellations, efficiently supporting satellite maneuvers for collision avoidance.

[0088] Furthermore, it should be noted that the present invention can be provided as a method, apparatus, or computer program product. Therefore, embodiments of the present invention can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Moreover, embodiments of the present invention can take the form of a computer program product implemented on one or more computer-usable storage media containing computer-usable program code.

[0089] Embodiments of the present invention are described with reference to flowchart illustrations and / or block diagrams of methods, terminal devices (systems), and computer program products according to embodiments of the invention. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, embedded processor, or other programmable data processing terminal device to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing terminal device, generate instructions for implementing the flowchart illustrations. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0090] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing terminal device to operate in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The functions specified in one or more boxes. These computer program instructions may also be loaded onto a computer or other programmable data processing terminal equipment to cause a series of operational steps to be performed on the computer or other programmable terminal equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable terminal equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0091] It should also be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or terminal device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or terminal device. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or terminal device that includes said element.

[0092] Finally, it should be noted that the above description represents a preferred embodiment of the present invention. It should be pointed out that although preferred embodiments have been described, those skilled in the art, once they understand the basic inventive concept of the present invention, can make various improvements and modifications without departing from the principles described herein. These improvements and modifications should also be considered within the scope of protection of the present invention. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the embodiments of the present invention.

Claims

1. A collision warning detection method for giant constellations, comprising the following steps: Step S1: Construct a collision risk set based on the design of the protected mega-constellation system; Step S2: Based on the constellation system design and collision risk set, determine the intersection points and times where collisions may occur, specifically including: Step S201: Calculate the perigee and apogee altitudes of the satellite / debris to identify the satellite / debris that has a collision puncture zone with the protected constellation orbital zone; Step S202: Determine the intersection points of each orbital plane or extended orbital plane of the protected constellation with each orbital ring in the collision risk set; Step S203: Based on the Keplerian laws and intersection points of satellite operation, determine the discrete time of the intersection point; Step S3: Using the first satellite-to-ground distance H1 of the risk source satellite / debris at the intersection point and the second satellite-to-ground distance H2 of the protected mega-constellation satellites, determine whether there is a collision risk. This specifically includes: Step S301: Within an orbital loop, calculate the first satellite-to-ground distance H1 between a risk source satellite / debris at the intersection point when it moves to the intersection point position based on ephemeris data; Step S302: Within the same orbital loop, select any protected satellite and calculate the distance H2 between the satellite and the ground when the protected satellite moves to the corresponding intersection point position based on the ephemeris data; Step S303: Determine whether |H1-H2| is greater than the collision detection threshold. If yes, it is considered that there is no collision risk. If no, proceed to step S304. Step S304: Using the discrete time of the intersection point, calculate the position coordinates of the risk source at the corresponding time, as well as the position coordinates of each satellite on the orbital plane; Step S305: Calculate the spatial distance between the risk source and each satellite, and determine whether the spatial distance is less than the collision detection threshold. If so, the risk source is an object with collision risk. Step S306: Filter and record objects with collision risk, and calculate the collision probability, collision approach time, and collision approach distance. Step S4: Execute steps S2 and S3 using a parallel computing strategy to complete the collision risk assessment of all risk source satellites / debris and satellites of protected mega-constellation systems within the collision risk set.

2. The method according to claim 1, characterized in that, In step S1, before constructing the collision risk set, the following steps are also included: Step S101: Determine the number of orbital height layers of the constellation system based on the design parameters of the protected mega-constellation; Step S102: Calculate the perigee and apogee of each sub-layer based on the orbital altitude and eccentricity of the giant constellation sub-layers; Step S103: Determine the height of the upper and lower bands of the orbital zone in which the constellation system is located.

3. The method according to claim 2, characterized in that, In step S1, the collision risk set is constructed, specifically including: Step S104: Calculate the perigee and apogee altitudes of the satellite / debris by loading on-orbit satellite / debris ephemeris data; Step S105: Identify satellites / debris with collision penetration zones in the protected constellation orbital zone, and construct a collision risk set for satellites / debris with collision penetration zones.

4. The method according to claim 3, characterized in that, In step S105, satellites / debris with collision-penetration zones that exist with the protected constellation orbital zone are identified, specifically including: If the apogee altitude of a satellite / debris is greater than the upper edge of the protected constellation's orbital band, and the perigee altitude is less than the upper edge, then there is a puncture zone between the satellite / debris and the protected constellation's orbital band. If the apogee altitude of a satellite / debris is greater than the lower edge of the protected constellation's orbital band, and the perigee altitude is less than the lower edge, then there is a puncture zone between the satellite / debris and the protected constellation's orbital band.

5. The method according to claim 3, characterized in that, Before performing step S2, the following is also included: The satellites of the protected mega-constellation system are reduced in dimensionality and classified according to their orbital planes; The satellites / debris in the collision risk set are reduced in dimension and classified according to their orbital planes; The satellites of the classified protected mega-constellation system are combined into orbital rings according to their orbital planes and the orbital planes of the classified collision risk sets of satellites / debris.

6. An electronic device, characterized in that, include: One or more processors, one or more memories, and one or more computer programs; wherein the processor is connected to the memory, and the one or more computer programs are stored in the memory, and when the electronic device is running, the processor executes the one or more computer programs stored in the memory to cause the electronic device to perform a collision warning detection method for a mega-constellation as described in any one of claims 1-5.

7. A computer-readable storage medium, characterized in that, Used to store computer instructions, which, when executed by a processor, implement a collision warning detection method for a giant constellation as described in any one of claims 1-5.

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