Description | Example | Return message | Group

SetState Cartesian

Set the state of a satellite or missile using Cartesian coordinates

Syntax

SetState <VehObjectPath> Cartesian {Propagator} {NoProp | {TimeInterval}} <StepSize> {CoordSystem} "<OrbitEpoch>" <X> <Y> <Z> <vX> <vY> <vZ> ["<CoordEpoch>"]

Related commands

Description

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.

The SetState Cartesian command is valid for Satellite and Missile only.

The {Propagator} parameter is case sensitive and must match the format used in the Satellite Orbit or Missile Trajectory Basic properties page.

ParameterDescription
{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>Enter this in seconds; it must be greater than or equal to 0.001 seconds.

If you select LOP propagator, the <StepSize> must be greater than or equal to one day (86164.09 seconds).

{CoordSystem}Enter any coordinate system supported by the vehicle's central body. All central bodies support Fixed, Inertial, J2000, ICRF, and TrueOfDate. TrueOfEpoch, TEMEOfDate, TEMEOfEpoch, MeanOfDate, MeanOfEpoch, B1950, AlignmentAtEpoch, ITRF2020, ITRF2014, ITRF2008, ITRF2005, and ITRF2000 are supported when the central body is Earth. MeanEarth, PrincipalAxes_440, PrincipalAxes_430, PrincipalAxes_421, etc. are supported when the central body is Moon.
"<OrbitEpoch>"For valid "<OrbitEpoch>" values, see Time Options.
<X>, <Y>, <Z>, <vX>, <vY> <vZ>Enter these values 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 STK receives the SetState Cartesian command specifying HPOP for {Propagator}, STK uses the HPOP force model data in the scenario. 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 you create a new vehicle via the Connect New Command, STK uses the default force model data.

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 even when STK cannot display the orbit track. Connect performs the same validation that occurs from the entry of state data via the user interface.

Examples

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

Return message

Group membership

This command belongs to the following group(s):

Vehicles

Version

10.1