| A format for expressing the Keplerian Elements of a satellite. It takes the form:
AAAAAAAAAAA
1 NNNNNU NNNNNAAA NNNNN.NNNNNNNN +.NNNNNNNN +NNNNN-N +NNNNN-N N NNNNN
2 NNNNN NNN.NNNN NNN.NNNN NNNNNNN NNN.NNNN NNN.NNNN NN.NNNNNNNNNNNNNN
Where:
Line 1
Satellite name
Line 2
Column Description
01-01 Line Number of Element Data
03-07 Satellite Number
10-11 International Designator (Last two digits of launch year)
12-14 International Designator (Launch number of the year)
15-17 International Designator (Piece of launch)
19-20 Epoch Year (Last two digits of year)
21-32 Epoch (Day number and fractional portion of the day)
34-43 First Time Derivative of the Mean Motion divided by 2.
or Ballistic Coefficient (Depending of ephemeris type)
45-52 Second Time Derivative of Mean Motion divided by 6. (Blank if N/A)
54-61 BSTAR drag term if GP4 general perturbation theory was used.
Otherwise, radiation pressure coefficient.
63-63 Ephemeris type
65-68 Element number
69-69 Check Sum (Modulo 10)
Line 3
Column Description
01-01 Line Number of Element Data
03-07 Satellite Number
09-16 Inclination Degrees
18-25 Right Ascension of the Ascending Node Degrees
27-33 Eccentricity (decimal point assumed)
35-42 Argument of Perigee Degrees
44-51 Mean Anomaly Degrees
53-63 Mean Motion Revs per day
64-68 Revolution number at epoch Revs
69-69 Check Sum (Modulo 10)
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