TLE Explanation:
Two rows of roots（TLE）These are data used by the North American Aerospace Defense Command (NORAD) to predict the position and velocity of satellites in Earth orbit. They are based on the SPG4 model and are widely used in software such as STK. TLEs consist of two lines, containing satellite number, orbital parameters, and time information, which are used for precise prediction of satellite trajectories.
For example, using the ASRTU-1 satellite, the TLE data is as follows:
ASRTU-1
1 61781U 24199AY 24345.90169400 .00013086 00000+0 54306-3 0 9993
2 61781 97.3802 210.1292 0019014 112.9575 247.3671 15.23809972 49320
Line number（1）: This indicates that this is the first line of data.
Satellite number（61781）Each satellite has a unique identification number.
International Identifier（U）: Indicates satellite classification. U indicates unclassified.
Launch year and launch number（24199AY）: 24 indicates the year of satellite launch (2024), 199 represents the launch sequence number, and AY is the launch batch identifier.
Timestamp（24345.90169400）: Represents the time of the TLE data, where 24 is the last two digits of the year, 345 is the date (the 345th day), and .90169400 represents the time of day (the day of the year, expressed in decimal notation, with the decimal part representing the time within the day).
Orbital rate of change (0.00013086): Indicates the rate at which the satellite's orbit is changing (in units of changes per orbit).
Orbital drag coefficient (00000 + 0): Represents the drag effect on the satellite's orbit.
Interstellar coefficient（54306-3）Describes the interference factors experienced by satellites in orbit, where the numerical values indicate that the impact is minimal.
Data quality indicators（0）: The quality of the indicator data; 0 indicates the default value.
Inspection point（9993）: Used for verifying the correctness of data
Line number（2）: This indicates that this is the second line of data.
Satellite number（61781）: Same as the first line, used to identify the satellite.
Track inclination angle（97.3802）: The angle between the satellite's orbital plane and the Earth's equatorial plane, measured in degrees (0-90 degrees indicates a prograde orbit [clockwise when viewed from the North Pole], and 90-100 degrees indicates a retrograde orbit).
Ascending point declination（210.1292）: This refers to the angle between the satellite's orbital plane and the Earth's equatorial plane, measured in degrees.
Track eccentricity（0019014）: The ratio of the distance from the center of the satellite's elliptical orbit to the Earth's center, divided by the semi-major axis of the orbit, describes the eccentricity of the orbit.
Nearby parameters（112.9575）: The angle, in degrees, at which a satellite is closest to Earth in its orbit.
Average anomaly（247.3671）: The satellite's position angle on its orbit, measured in degrees.
Average orbital period (15.23809972 49320): The number of times a satellite orbits the Earth per day, with 15.23809972 49320 indicating approximately 15.23 orbits per day.
Reference materials:https://eslab.dgut.edu.cn/river/detail/article/29/sciences
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