Path: Orbit/OrbitCoord
% Convert NORAD TLE string into a data structure.
Can process two or three-line version of elements. Three-line elements
are determined by a line with a first character that is not a number
(traditionally the spacecraft's name), example:
Mir
1 16609U 86017A 97059.07924160 .00056468 00000-0 66860-3 0 879
2 16609 51.6505 274.3828 0011764 122.9249 237.3208 15.60613928629999
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Form:
x = ConvertNORAD( a, threeLine )
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Inputs
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a (:,1) Data, file name or string
threeLine (1) Boolean to force three-line format
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Outputs
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x (n) Data structure
.satelliteNumber Object ID
.launchYear Year (part of international designator)
.launchNumber Launch number
.launchpiece Launch piece
.epochYear Two/one digit epoch year
.epochDay Epoch day number
.n0Dot 1st Derivative of the Mean Motion (rad/min^2)
.n0DDot 2nd Derivative of the Mean Motion
.bStar Adjusted ballistic coefficient
.i0 Inclination (rad)
.f0 Right Ascension of Ascending Node (rad)
.e0 Eccentricity
.w0 Argument of Perigee (rad)
.M0 Mean Anomaly (rad)
.n0 Mean Motion (rad/min)
The following fields are computed from the element data.
.ballisticCoeff Ballistic coefficient (m2/kg)
.julianDate Epoch Julian date
.fullLaunchYear Four digit launch year
.sma Semi-major axis (km)
n (1,1) Number of element sets
t (3,n) Time information if present on second line
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Common: Time/Date2JD
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