To calculate the position of the object around the earth, for example, satellites and space debris, we need information on the orbital parameters which describes the shape and size of the orbit. Two-Line Element Set is one of the data formats for describing the orbital parameters.
In this article, we explain TLE and its format overview.
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What is Two-Line Element Set?
Two Line Element Set (TLE) is the data format to describe the orbital parameters of the earth-orbiting object. The example of TLE for ISS:
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
First line is Line 0, thus this is called two-line element set.
Then, for each element.
Object Name
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
Line 0 includes only the object name (maximum 24 characters).
ISS means International Space Station, ZARYA is the first module of ISS, which has launched in 1998.
Type description follows this object name, i.e. R/B for rocket bodies, DEB for space debris.
The following TLE is about the upper stage of the H-IIA rocket in Japan:
H-2A R/B 1 38341U 12025E 21080.34754647 .00000316 00000-0 44249-4 0 9997 2 38341 98.5245 259.8111 0056444 63.1730 297.5239 14.84192015478432
China has conducted an anti-satellite missile test in 2007, which destroyed Fengyun-1C and generated a lot of fragment debris. This is one of the fragments of Fengyun-1C.
FENGYUN 1C DEB 1 29733U 99025X 21080.32325869 .00000063 00000-0 17212-3 0 9993 2 29733 99.2303 24.6693 0578834 210.4520 307.7773 12.92087092667824
We can tell the type of object.
Line Number
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
The first column is line number.
Satellite Catalog
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
This is the satellite catalog number, that is, consecutive assigned number for launched object.
The world’s first satellite, Sputnik 1 is assigned the catalog number 00002. The upper stage of the launch rocket is assigned 00002.
Secutiry Classification
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
This field is security classification.
U means Unclassified, All of publicly available TLEs have U in this field.
It is said that S is set in this field for the non-public objects, such as military satellites, however, we cannot see it.
International Designator
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
the two lower digits of launch year, the number of launch (3 numbers), identification of launched object (1-3 characters).
This TLE indicates that this object was launched in 1998, 67th, object A.
FENGYUN 1C DEB 1 47041U 99025FBT 21078.22908376 .00000829 00000-0 19377-3 0 9995 2 47041 98.1863 64.2148 0034562 278.0092 93.2342 14.56898177457720
Fragments generated from Fengyun 1C are identified by this.
Epoch
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
TLE includes the orbital parameters of satellites, the reference time is needed.
The reference time for orbital parameters is called an epoch.
In order, the two lower digits of epoch year, the elapsed time from noon of January 1st in that year.
In this situation, 300.83097691 days in 2020.
Note that this is in UTC.
First Time Derivative of the Mean Motion
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
This is the first time derivative of the mean motion divided by two (in rev/day^2).
Second Time Derivative of the Mean Motion
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
This is the second time derivative of the mean motion divided by 6 (in rev/day^3).
This is a small number, almost all TLEs have 00000-0 in this field.
BSTAR Drag Term
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
This is drag coefficient used in SGP4.
Ballistic coefficient B is described as
[B = frac{C_D A}{m}]
where (C_D) is drag coefficient, (A) is cross sectional area, (m) is mass.
Ballistic coefficient denotes how objects be affected by drag. The bigger this value, The more effect.
(B*) is complement of B using atmospheric density (rho_0),
[B* = frac{Brho_0}{2}]
Ephemeris type
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
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This number describes the ephemeris model used for the calculation of orbital elements.
1=SGP, 2=SGP4, 3=SDP4, 4=SGP8, 5=SDP8
However, this field is 0 in all public data, the orbital elements are calculated by using SGP4/SDP4.
Element number
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
This number is incremented by updating this information.
However, this number is fixed at 999.
Checksum
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
The last field of each line is the checksum for detecting data errors.
This number is the remainder after dividing the sum of all the numbers in a line by 10, ignoring characters, spaces, periods, and plus symbols. Only minus signs are treated as -1.
Inclination
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
Inclination in degree．
Right Ascension of the Ascending Node
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
Right ascnsion of the ascending node in degree．
Eccentricity
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
Eccentricity. The decimal point is omitted. In this case, the eccentricity is 0.0001671.
Argument of Perigee
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
Argument of perigee in degree．
Mean Anomaly
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
Mean motion in degree．
Mean Motion
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
Mean motion in Rev/day．
Revolution number at epoch
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ISS (ZARYA) 1 25544U 98067A 20300.83097691 .00001534 00000-0 35580-4 0 9996 2 25544 51.6453 57.0843 0001671 64.9808 73.0513 15.49338189252428
This is the revolution number at epoch. Note that this field shows only the five lower digits.
Summary
These TLEs are managed by NORAD and published.
https://www.celestrak.com/NORAD/elements/
Source: https://t-tees.com
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