Set the orbit state of a satellite using a two-line element set.
SetState <SatObjectPath> TLE "<TLECard1>" "<TLECard2>" [{Options}]
The SetState TLE command sets the orbit state of the specified satellite, using the input two-line element set, and propagates the orbit. When specifying the TLE Cards, use the entire card, including spaces, and enclose each card in double quotes.
Note: Each TLE Card must be 69 characters long. Do not leave out any spaces.
The following {Options} can be included on the command line:
| {Options} | Description |
|---|---|
| TimePeriod {TimeInterval} | The span of the ephemeris. If not
entered, then the time period is obtained from the TLE card.
For valid {TimeInterval} values see Time Options. |
| TimeStep <StepSize> | The interval between calculated ephemeris output points. Entered in seconds |
| Routine <PropName> | This option allows for the selection of a different implementation of the SGP4 routine for propagating ephemeris for this satellite. For more information on changing SGP4 routines see the SetSGP4Prop command. |
| NoProp | If included on the command line the satellite's state will be set but it will not be propagated. |
Set Satellite1 to use the specified two-line element set:
SetState */Satellite/Satellite1 TLE "1 10637U 78012A 04113.40484266 .00000000 00000-0 10000-3 0 9453" "2 10637 40.1939 40.6913 1575431 119.1582 257.4005 1.00053877 48625"
Set Satellite2 to use the specified two-line element set, and propagate over the input time period:
SetState */Satellite/Satellite2 TLE "1 10637U 78012A 04113.40484266 .00000000 00000-0 10000-3 0 9453" "2 10637 40.1939 40.6913 1575431 119.1582 257.4005 1.00053877 48625" TimePeriod "1 Jun 2004 12:00:00.00" "1 Jun 2004 18:00:00.00"
If activated, Connect returns an acknowledgement message.
This command belongs to the following group(s):
10.1
STK Programming Interface 11.0.1