A spacecraft collision warning method for mass space targets
By combining screening and parallel processing methods, a large number of spatial targets are preliminarily screened and analyzed in detail, solving the problem of high computational load in existing technologies and achieving efficient collision warning and risk assessment.
Patent Information
- Application Number
- CN202610373730.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-03-25
- Publication Date
- 2026-07-10
AI Technical Summary
When performing collision warnings for massive spatial targets, the commonly used perigee-apogee height screening method can effectively filter out some targets that cannot intersect, but a large number of targets that cannot intersect still fail to be filtered out, resulting in high computational load and low efficiency.
A combination of date expiration pre-screening, apogee/perigee pre-screening, orbital intersection pre-screening, and time pre-screening, along with a parallel screening and early warning method, is used to perform preliminary screening of massive spatial targets, reducing the computational load for subsequent orbital prediction. Detailed analysis is then conducted using the SGP4 orbital model and collision probability model.
It effectively filters out targets that cannot intersect, reduces computational load, and quickly generates collision warning information, making it easier for users to understand risks and formulate avoidance strategies in a timely manner.
Smart Images
Figure CN122365823A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of spacecraft collision warning technology, and more specifically to a spacecraft collision warning method for a large number of space targets. Background Technology
[0002] In recent years, advancements in space technology have lowered the barriers to accessing and using space, leading to a surge in the number of space launches and space targets. Over 29,000 space targets have been cataloged in orbit, posing a threat to spaceflight safety and operations. Due to the extremely high relative speeds between spacecraft and space targets, even small pieces of space debris can cause catastrophic damage, while large debris necessitates spacecraft maneuvers to ensure safety. Therefore, it is crucial to utilize real-time orbital data for spacecraft proximity analysis and collision warnings, providing early warnings of high-risk events and a basis for evasive maneuvers.
[0003] Currently, collision warning systems first predict the orbit of each space target epoch and then calculate the approach distance, which involves a large amount of computation. It is necessary to quickly screen targets that may pose a rendezvous risk before further analysis. While the commonly used perigee-apogee altitude screening method can effectively eliminate some targets that are unlikely to intersect with the spacecraft, a large number of targets that are unlikely to intersect with the spacecraft still fail to be screened. Summary of the Invention
[0004] The purpose of this invention is to solve the technical problem that although the commonly used perigee-apogee height screening method can effectively screen out some targets that cannot intersect with the spacecraft, a large number of targets that cannot intersect with the spacecraft are still not screened out. The invention provides a spacecraft collision early warning method for a large number of space targets.
[0005] To solve the above-mentioned technical problems, the technical solution provided by the present invention is as follows: A spacecraft collision early warning method for a large number of space targets includes the following steps: S1. Retrieve the collision target orbit TLE data set and the collision complete set from the aerospace database; S2, set the pre-screening threshold for date expiration, the safety margin for pre-screening at apogee / perigee, the pre-screening threshold for track intersection, the pre-screening threshold for time, and the calculation step size; S3. Based on the number of main target orbits in the collision main target orbit TLE data set and the processor's processing capability, select the appropriate multi-data parallel filtering early warning method and execute steps S4 to S6. That is, each thread of the processor performs filtering and early warning on one primary target track in the collision primary target track tle data set and all secondary target tracks in the collision complete set tle data set; S4. Based on the date expiration pre-screening threshold, apogee / perigee pre-screening safety margin, track intersection pre-screening threshold, and time pre-screening threshold, filter the target tracks within the collision set TLE data set to obtain the initial target tracks; S5. Set the start and end times for the SGP4 satellite orbit model to predict the SGP4 orbit, and combine the calculation step size to form a time series for SGP4 orbit prediction. The initial screening results will be sent from the target orbit to the SGP4 satellite orbit model; The SGP4 satellite orbit model is used to predict the main target orbit and the initially screened secondary target orbits at each moment in the time series. This yields the spatial positions of the spacecraft in the main target orbit and the spacecraft in the initially screened secondary target orbits at all moments, as well as their velocities at their current spatial positions. Based on the spatial positions of the spacecraft in the main target orbit and the spacecraft in the initially screened secondary target orbits at all moments in the time series, the minimum spatial distance between the two spacecraft is obtained. Input the space position, the velocity at the current space position, and the spacecraft's equivalent collision radius into the collision probability model. The collision probability model calculates and outputs the collision probability between the spacecraft in the main target orbit and the spacecraft in the initially screened secondary target orbit. S6. Summarize the numbering information of the main target orbit and the secondary target orbit, as well as the minimum spatial distance between the main target orbit and the secondary target orbit, the collision probability, and the time corresponding to the minimum spatial distance into a collision warning result; S7. Summarize all collision warning results obtained from parallel screening and output a set of collision warning information that characterizes the probability of collision between a spacecraft in the main target orbit and multiple spacecraft in the secondary target orbits in the future time period.
[0006] Furthermore, in step S4, the specific method for filtering the target orbits within the collision set orbit TLE data set by setting a pre-screening threshold for date expiration is as follows: The epoch date of the target orbit within the collision set orbit tle data set is compared with the date expiration pre-screening threshold. If the epoch date of the target orbit is too far from the date expiration pre-screening threshold, the target orbit is removed. Otherwise, the target track should be pre-filtered by date expiration.
[0007] Furthermore, in step S4, the specific method for screening the target orbit within the collision full set orbit TLE data set using the set apogee / perigee pre-screening safety margin is as follows: Obtain the apogee and perigee altitudes of the primary target orbit, as well as the apogee and perigee altitudes of the secondary target orbit; If the sum of the apogee altitude of the primary target orbit and the apogee / perigee pre-screening safety margin is less than the perigee altitude of the secondary target orbit, or if the sum of the apogee altitude of the secondary target orbit and the apogee / perigee pre-screening safety margin is less than the perigee altitude of the primary target orbit, then the primary target orbit and the secondary target orbit cannot intersect in terms of spatial altitude, and the secondary target orbit is eliminated. Otherwise, the target orbit should be pre-screened via apogee / perigee.
[0008] Furthermore, in step S4, the specific method for filtering the target orbits within the collision set's TLE data set using the set orbit intersection pre-screening threshold is as follows: Calculate the minimum spatial geometric distance between the primary target orbit and the secondary target orbit at the intersection line in the orbital plane; If the minimum spatial geometric distance is greater than the set pre-screening threshold for track intersection, then the target track is rejected. Otherwise, pre-screening should be performed from the target track via track intersections.
[0009] Furthermore, in step S4, the specific method for filtering the target orbits within the collision set orbit TLE data set by setting a time pre-screening threshold is as follows: Obtain the intersection points between the primary target orbit and the secondary target orbit within the collision set TLE data set, which are pre-filtered by orbit intersection lines; The first time when the spacecraft in the main target orbit arrives at the orbital intersection point, and the second time when the spacecraft in the target orbit arrives at the same orbital intersection point, are obtained respectively. The time difference between the first time and the second time is calculated. If the absolute value of the time difference is greater than the set time pre-screening threshold, it means that the time interval between the two spacecraft passing through the intersection point is long enough and there is no possibility of collision. The spacecraft from the target orbit is then removed. Otherwise, the target trajectory should be pre-screened by time.
[0010] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. The spacecraft collision early warning method for massive space targets provided by this invention filters the target orbits in the TLE data set of the collision set by setting a pre-screening threshold for date expiration, apogee / perigee pre-screening safety margin, orbit intersection pre-screening threshold, and time pre-screening threshold. That is, it adopts a combination of pre-screening for date expiration, apogee / perigee, orbit intersection, and time pre-screening, which can filter out targets that are impossible to intersect with the spacecraft to the greatest extent and reduce the computational load of subsequent orbit prediction.
[0011] 2. The spacecraft collision early warning method for massive space targets provided by this invention adopts a parallel screening and early warning approach, which can simultaneously screen, predict, and calculate the collision probability of multiple target orbits within the collision full set orbit TLE data set. This helps to quickly generate collision early warning set information, allowing users to quickly understand whether the target of their interest is at risk of colliding with other space targets, and thus react quickly and formulate relevant avoidance strategies in advance. Attached Figure Description
[0012] Figure 1 This is a schematic diagram of the parallel screening and early warning process in an embodiment of the present invention. Detailed Implementation
[0013] The technical solutions of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.
[0014] like Figure 1 As shown, a spacecraft collision early warning method for a large number of space targets includes the following steps: 1) Retrieve the TLE data set of the primary target orbit and the TLE data set of the complete collision dataset from the aerospace database; 2) Set the pre-screening threshold for date expiration, the safety margin for pre-screening at apogee / perigee, the pre-screening threshold for track intersection, the pre-screening threshold for time, and the calculation step size; 3) Based on the number of primary target orbits in the collision primary target orbit TLE data set and the processor's processing capability, select the appropriate multi-data parallel filtering and early warning method, and execute steps 4) to 6). Essentially, each thread of the processor corresponds to a primary target track and a collision set, filtering and alerting all secondary target tracks within the TLE data set; the more processor threads there are, the more primary and secondary target tracks can be filtered and alerted in parallel.
[0015] 4) Compare the epoch date of the target orbit within the collision set orbit tle data set with the date expiration pre-screening threshold. If the epoch date of the target orbit is too far from the date expiration pre-screening threshold, then remove the target orbit. Otherwise, pre-filter the target track by date expiration; The specific method for filtering target orbits within the entire TLE dataset based on the pre-screened apogee / perigee safety margin is as follows: Obtain the apogee and perigee altitudes of the primary target orbit, as well as the apogee and perigee altitudes of the secondary target orbit; If the sum of the apogee altitude of the primary target orbit and the apogee / perigee pre-screening safety margin is less than the perigee altitude of the secondary target orbit, or if the sum of the apogee altitude of the secondary target orbit and the apogee / perigee pre-screening safety margin is less than the perigee altitude of the primary target orbit, then the primary target orbit and the secondary target orbit cannot intersect in terms of spatial altitude, and the secondary target orbit is eliminated. Otherwise, the target orbit should be pre-screened via apogee / perigee. The specific method for filtering target tracks within the TLE dataset of the entire collision set using a pre-screening threshold value for track intersection is as follows: Calculate the minimum spatial geometric distance between the primary target orbit and the secondary target orbit at the intersection line in the orbital plane; If the minimum spatial geometric distance is greater than the set pre-screening threshold for track intersection, then the target track is rejected. Otherwise, pre-screening should be performed from the target track through the track intersection line; The specific method for filtering target orbits within the collision full set orbit TLE data set using a set time pre-screening threshold is as follows: Obtain the intersection points between the primary target orbit and the secondary target orbit within the collision set TLE data set, which are pre-filtered by orbit intersection lines; The first time when the spacecraft in the main target orbit arrives at the orbital intersection point, and the second time when the spacecraft in the target orbit arrives at the same orbital intersection point, are obtained respectively. The time difference between the first time and the second time is calculated. If the absolute value of the time difference is greater than the set time pre-screening threshold, it means that the time interval between the two spacecraft passing through the intersection point is long enough and there is no possibility of collision. The spacecraft from the target orbit is then removed. Otherwise, the target trajectory should be pre-screened by time. 5) Set the start and end times for the SGP4 satellite orbit model to predict the SGP4 orbit, and combine the calculation step size to form a time series for SGP4 orbit prediction; The initial screening results will be sent from the target orbit to the SGP4 satellite orbit model; The SGP4 satellite orbit model is used to predict the main target orbit and the initially screened secondary target orbits at each moment in the time series. This yields the spatial positions of the spacecraft in the main target orbit and the spacecraft in the initially screened secondary target orbits at all moments, as well as their velocities at their current spatial positions. Based on the spatial positions of the spacecraft in the main target orbit and the spacecraft in the initially screened secondary target orbits at all moments in the time series, the minimum spatial distance between the two spacecraft is obtained. Input the space position, the velocity at the current space position, and the spacecraft's equivalent collision radius into the Patra collision probability model. The Patra collision probability model calculates and outputs the collision probability between the spacecraft in the main target orbit and the spacecraft in the initially screened secondary target orbit. 6) The numbering information of the primary target orbit and the secondary target orbit, as well as the minimum spatial distance between the primary target orbit and the secondary target orbit, the collision probability, and the time corresponding to the minimum spatial distance are summarized into a collision warning result; 7) Summarize all collision warning results obtained from parallel screening and output a set of collision warning information that characterizes the probability of collision between a spacecraft in the main target orbit and multiple spacecraft in the secondary target orbits in the future time period.
[0016] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions within the technical scope disclosed in the present invention should be covered within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.
Claims
1. A spacecraft collision early warning method for a large number of space targets, characterized in that, Includes the following steps: S1. Retrieve the collision target orbit TLE data set and the collision complete set from the aerospace database; S2, set the pre-screening threshold for date expiration, the safety margin for pre-screening at apogee / perigee, the pre-screening threshold for track intersection, the pre-screening threshold for time, and the calculation step size; S3. Based on the number of main target orbits in the collision main target orbit TLE data set and the processor's processing capability, select the appropriate multi-data parallel filtering early warning method and execute steps S4 to S6. That is, each thread of the processor performs filtering and early warning on one primary target track in the collision primary target track tle data set and all secondary target tracks in the collision complete set tle data set; S4. Based on the date expiration pre-screening threshold, apogee / perigee pre-screening safety margin, track intersection pre-screening threshold, and time pre-screening threshold, filter the target tracks within the collision set TLE data set to obtain the initial target tracks; S5. Set the start and end times for the SGP4 satellite orbit model to predict the SGP4 orbit, and combine the calculation step size to form a time series for SGP4 orbit prediction. The initial screening results will be sent from the target orbit to the SGP4 satellite orbit model; The SGP4 satellite orbit model is used to predict the main target orbit and the initially screened secondary target orbits at each moment in the time series, so as to obtain the spatial position of the spacecraft in the main target orbit and the spacecraft in the initially screened secondary target orbit at all moments, as well as the velocity at the current spatial position. Based on the spatial positions of the spacecraft in the main target orbit and the spacecraft in the initially screened secondary target orbit at all times in the time series, the minimum spatial distance between the two spacecraft is obtained. Input the space position, the velocity at the current space position, and the spacecraft's equivalent collision radius into the collision probability model. The collision probability model calculates and outputs the collision probability between the spacecraft in the main target orbit and the spacecraft in the initially screened secondary target orbit. S6. Summarize the numbering information of the main target orbit and the secondary target orbit, as well as the minimum spatial distance between the main target orbit and the secondary target orbit, the collision probability, and the time corresponding to the minimum spatial distance into a collision warning result; S7. Summarize all collision warning results obtained from parallel screening and output a set of collision warning information that characterizes the probability of collision between a spacecraft in the main target orbit and multiple spacecraft in the secondary target orbits in the future time period.
2. The spacecraft collision early warning method for massive space targets according to claim 1, characterized in that, In step S4, the specific method for filtering the target orbits within the collision set orbit TLE data set by setting a pre-screening threshold for date expiration is as follows: The epoch date of the target orbit within the collision set orbit tle data set is compared with the date expiration pre-screening threshold. If the epoch date of the target orbit is too far from the date expiration pre-screening threshold, the target orbit is removed. Otherwise, the target track should be pre-filtered by date expiration.
3. The spacecraft collision early warning method for massive space targets according to claim 1, characterized in that, In step S4, the specific method for filtering the target orbit within the collision full set orbit TLE data set using the set apogee / perigee pre-screening safety margin is as follows: Obtain the apogee and perigee altitudes of the primary target orbit, as well as the apogee and perigee altitudes of the secondary target orbit; If the sum of the apogee altitude of the primary target orbit and the apogee / perigee pre-screening safety margin is less than the perigee altitude of the secondary target orbit, or if the sum of the apogee altitude of the secondary target orbit and the apogee / perigee pre-screening safety margin is less than the perigee altitude of the primary target orbit, then the primary target orbit and the secondary target orbit cannot intersect in terms of spatial altitude, and the secondary target orbit is eliminated. Otherwise, the target orbit should be pre-screened via apogee / perigee.
4. The spacecraft collision early warning method for massive space targets according to claim 1, characterized in that, In step S4, the specific method for filtering the target orbits within the collision set's TLE data set using the set orbit intersection pre-screening threshold is as follows: Calculate the minimum spatial geometric distance between the primary target orbit and the secondary target orbit at the intersection line in the orbital plane; If the minimum spatial geometric distance is greater than the set pre-screening threshold for track intersection, then the target track is rejected. Otherwise, pre-screening should be performed from the target track via track intersections.
5. The spacecraft collision early warning method for massive space targets according to claim 1, characterized in that, In step S4, the specific method for filtering the target orbits within the collision set orbit TLE data set by setting a time pre-filtering threshold is as follows: Obtain the intersection points between the primary target orbit and the secondary target orbit within the collision set TLE data set, which are pre-filtered by orbit intersection lines; The first time when the spacecraft in the main target orbit arrives at the orbital intersection point, and the second time when the spacecraft in the target orbit arrives at the same orbital intersection point, are obtained respectively. The time difference between the first time and the second time is calculated. If the absolute value of the time difference is greater than the set time pre-screening threshold, it means that the time interval between the two spacecraft passing through the intersection point is long enough and there is no possibility of collision. The spacecraft from the target orbit is then removed. Otherwise, the target trajectory should be pre-screened by time.