Name
|
Description
|
ClassNum
|
Integer giving the classification number of the TLE set.
|
DeclaredName
|
The name of the object as declared.
|
DisplayName
|
The name displayed for this object in output windows such as views, plots, and reports.
|
ElsetNum
|
Integer giving the element number.
|
EphTp
|
Integer giving the ephemeris type.
|
EpochDay
|
Real number giving the days and fraction of day of the TLE epoch.
|
EpochYear
|
Integer giving the year of the TLE epoch.
|
FKCon
|
The FK constant value.
|
GravCon
|
The gravity model to use.
|
NDdt
|
The second derivative of the mean motion. The TLE set contains the value of the second derivative and its exponent as two separate values. On input, they are combined to get the actual value, and this is stored in NDdt. Then 0 is stored in NDdtExp.
|
NDot
|
First derivative of the mean motion. The TLE set contains the value of the derivative and its exponent as two separate values. On input, they are combined to get the actual value, and this is stored in NDot. Then 0 is stored in NDotExp.
|
ObjectId
|
The unique identifier for the object.
|
ObjectType
|
The type of the object.
|
ResetCartesian
|
After setting the value of one or more properties of the NoradSGP4State child object of the Spacecraft in script, this property must be called. This will convert the NoradSGP4 elements to Cartesian and set the state of the Spacecraft. This step must be taken for the propagator to function correctly, whenever NoradSGP4State properties are modified in the script. Example:
Spacecraft1.NoradSGP4.I = 20.0; // set inclination to 20 degrees
Spacecraft1.NoradSGP4.E = 0.001; // set eccentricity
Spacecraft1.ResetCartesian = 1; // update Spacecraft state
|
RevNo
|
Integer giving the revolution number at the epoch of the TLE set.
|
SatName
|
String giving the satellite name for the TLE set.
|
SatNum
|
Integer giving the satellite number of the TLE set.
|
StepSize
|
The number of seconds the propagated object is advanced when the Step command is executed.
|
