[G ECI] = propTLE(TLE,startTime,elapsedTime,[GEOM]); [pos vel time] = propTLE(TLE,startTime,elapsedTime);
Parameters |
Description |
TLE [struct] |
TLE structure from TLEExtract |
startTime [date] |
Start time (in UT1) - can be any acceptable Matlab date format. If empty, startTime is the TLE Epoch Date. |
elapseTime [vector] |
Time vector for propagation from startTime or length of time to propagate from startTime (sec) |
GEOM [struct/list] |
(Optional) Geometry structure defining observer position and velocity as from GeomStruct or a list of (RPLLA,[VPLLA],[RE]). Defaults to LLA position and velocity equal [0 0 0]. |
RPLLA [vector] |
(Optional) Observer LLA position [Lat Long Alt] |
VPLLA [vector] |
(Optional) Observer LLA velocity [Vxy Heading Vz] |
RE [scalar/vector] |
(Optional) Earth radius, defaults to PhysicalConst('reequator','repole') |
Return Values |
Description |
G [struct] |
Array of ECF geometry structures |
ECI [struct] |
Contains the satellite position, velocity, and time data |
ECI.pos [array] |
X, Y, Z position data (m) |
ECI.vel [array] |
X, Y, Z velocity data (m/s) |
ECI.time [array] |
Time required for conversion from ECI to ECF (sec) |
pos [array] |
X, Y, Z position data in ECI coordinates (m) |
vel [array] |
X, Y, Z velocity data in ECI coordinates (m/s) |
time [array] |
Time required for conversion from ECI to ECF (sec) |
Copyright (c) 2009. All rights reserved.
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