Path: Orbit/OrbitMechanics
% Propagates a set of NORAD two line elements with a common time frame.
For each each TLE set, Propagate TLE is called with the appropriate
"tVec" input so that the starting epoch of all trajectories is "jD0".
If "jD0" is empty, the latest Julian date of the given TLEs is used.
See also NORAD, LoadNORAD, ConvertNORAD, PropagateTLE
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Form:
[r,v,x] = PropagateTLECommonTime( jD, tVec, file, model )
[r,v,x] = PropagateTLECommonTime( jD, tVec, x, model )
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Inputs
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jD0 (1,1) Epoch Julian date for all TLEs
tVec (1,:) Time vector (sec). Referenced to jD0.
file (1,:) File name OR converted data structure
model (1,:) Model type 'SGP', 'SGP4', 'SDP4', 'SGP8', 'SGD8'
The default model is SGP4.
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Outputs
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r (3,:) or {:} Position vectors
v (3,:) or {:} Velocity vectors
x (:) Structure of NORAD element data
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References: Hoots, F. R. and R. L. Roehrich, "Spacetrack Report No. 3:
Models for Propagation of NORAD Element Sets", Dec. 1980.
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Orbit: OrbitCoord/ConvertNORAD Orbit: OrbitMechanics/PropagateTLE SC: Ephem/GMSTime SC: Ephem/MSidDay Common: Time/DTSToDTA Common: Time/Date2JD Common: Time/JD2000 Common: Time/JDToMidnight Math: MathUtils/R2P5
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