Set the state of a satellite or missile using Cartesian coordinates
SetState <VehObjectPath> Cartesian {Propagator} {NoProp | {TimeInterval}} <StepSize> {CoordSystem} "<OrbitEpoch>" <X> <Y> <Z> <vX> <vY> <vZ> ["<CoordEpoch>"]
The SetState Cartesian command sets the orbit state of the specified satellite or missile and propagates the orbit over the specified time period. The propagated ephemeris data is spaced by the <StepSize> parameter.
Note: The SetState Cartesian command is valid for Satellite and Missile only.
Warning: {Propagator} and {CoordSystem} parameters are case sensitive and must match the format used in the Satellite Orbit or Missile Trajectory Basic properties page.
| Parameter | Description |
|---|---|
| {Propagator} | This parameter is case sensitive and
the Propagator name must match the format used in the Satellite's
Orbit page or Missile's Trajectory page under Basic properties.
Valid values for Satellite are TwoBody, J2Perturbation, J4Perturbation, HPOP and LOP. Valid values for Missile are TwoBody and HPOP. |
| {NoProp | {TimeInterval}} |
Enter NoProp to set the state of the vehicle but not propagate it. Enter {TimeInterval} to define the beginning and end of the satellite's time period for propagation. For valid {TimeInterval} values see Time Options. |
| <StepSize> | Entered in seconds and must be greater
or equal to 0.001 seconds.
Note: If LOP propagator is selected, the <StepSize> must be greater or equal to one day (86164.09 seconds). |
| {CoordSystem} | This parameter is case sensitive and the CoordSystem name must match the format used in the Orbit page of the vehicle's Basic properties. Valid Values are ICRF, J2000, MeanOfDate, MeanOfEpoch, TrueOfDate, TrueOfEpoch, B1950, TEMEOfDate, TEMEOfEpoch, AlignmentAtEpoch. |
| "<OrbitEpoch>" | For valid "<OrbitEpoch>" values see Time Options. |
| <X>, <Y>, <Z>, <vX>, <vY> <vZ> | These values are entered using Connect distance units. |
| ["<CoordEpoch>"] | This parameter is only applicable, and
is required, for {CoordSystem} based on an Epoch, such as
MeanOfEpoch, TrueOfEpoch, TEMEOfEpoch and AlignmentAtEpoch.
For valid "<CoordEpoch>" values see Time Options. |
Propagator-specific parameters stored with the vehicle's instance aren't affected. For example, when the SetState Cartesian command is received and an HPOP {Propagator} is specified, the existing HPOP force model data is used. If you create a vehicle and modify the force model, or load a vehicle with a modified force model, that data isn't modified by this command. If a new vehicle is created via the Connect New Command, the default force model data is used.
Warning: The STK orbit propagator doesn't completely validate the correctness of the complete Orbit State specified. This means that Connect may return a positive acknowledgment when the orbit track can't be displayed. Connect performs the same validation that occurs from the entry of state data via the user interface.
To set the orbit for the ERS1 satellite using Cartesian coordinates:
SetState */Satellite/ERS1 Cartesian J4Perturbation "1 Nov 2000 00:00:00.00" "1 Nov 2000 08:00:00.00" 60 J2000 "1 Nov 2000 00:00:00.00" -5465000.513055 4630000.194365 0.0 712.713627 841.292034 7377.687805
To set the orbit for Satellite2 using Cartesian coordinates:
SetState */Satellite/Satellite2 Cartesian LOP "1 Oct 1999 00:00:00.00" "30 Nov 1999 00:00:00.00" 86164.1 B1950 "1 Oct 1999 00:00:00.00" -986500 -42152457. 364.8 3073.7 -0071.9 -0014.9
To set the state for Missile1 using Cartesian coordinates and the TwoBody propagator:
SetState */Missile/Missile1 Cartesian TwoBody "1 Jul 2005 12:00:00.00" "2 Jul 2005 12:00:00.00" 60 J2000 "1 Jul 2005 12:00:00.00" -1060108.957514 6289419.72631631 308.528931 -3243.949097 4906.621760 1844.826709
To set the orbit for the Satellite2 satellite using Cartesian coordinates:
SetState */Satellite/ERS1 Cartesian J4Perturbation "Scenario/Scenario1 AnalysisStartTime" "+6 hours" 60 J2000 "Scenario/Scenario1 AnalysisStartTime" -5465000.513055 4630000.194365 0.0 712.713627 841.292034 7377.687805
If activated, Connect returns an acknowledgement message.
This command belongs to the following group(s):
10.1
STK Programming Interface 11.0.1