SetState Classical
Set the orbit state of a satellite or missile using classical coordinates
Syntax
SetState <VehObjectPath> Classical {Propagator} {NoProp | {TimeInterval}} <StepSize> {CoordSystem} "<OrbitEpoch>" <SemiMajorAxis> <Eccentricity> <Inclination> <ArgOfPerigee> <RAAN> <MeanAnom> ["<CoordEpoch>"]
Related commands
Description
The SetState Classical command sets the orbit state of the specified satellite or missile, using the input classical element set, and propagates the orbit over the specified time period. The propagated ephemeris data is spaced by the <StepSize> parameter.
The SetState Classical command is valid for Satellite and Missile only.
| 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.
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. |
| <SemiMajorAxis> | Entered in Connect distance units. |
| <Eccentricity> | A real number greater or equal to 0.0 and less than 1.0 |
| <Inclination> | Entered in degrees. |
| <ArgOfPerigee> | Entered in degrees. |
| <RAAN> | Entered in degrees. |
| <MeanAnom> | Entered in degrees. |
| ["<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. |
This command doesn't accept values of less than -180 degrees for orbital elements.
Propagator-specific parameters stored with the vehicle instance aren't affected. For example, when the SetState Classical 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.
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.
Examples
To set the path for the ERS1 satellite using Classical coordinates and propagate the orbit:
To set the path for the ERS1 satellite using Classical coordinates and propagate the orbit:
To set the path for a satellite, named Molniya, traveling in a Molniya orbit and propagate the orbit:
To set the state for Missile1 using Classical coordinates and the TwoBody propagator:
To set the path for the ssClass6 satellite using Classical coordinates and propagate the orbit over the Scenario's analysis time period:
Return message
Group membership
This command belongs to the following group(s):
Version
10.1