Description | Example | Return message | Group

SetState (Missile)

Set the trajectory of a missile using the TwoBody propagator.

Syntax

SetState <MissileObjectPath> {CoordinateType} TwoBody {TimeInterval} <StepSize> {CoordSystem} "<OrbitEpoch>" <CoordTypeParameters> ["<CoordEpoch>"]

Related commands

SetState

Description

The SetState command for Missiles sets the trajectory of the specified missile. The propagated ephemeris data is spaced by the <StepSize> parameter.

Two-Body is an analytical propagator that generates ephemeris by evaluating a formula. Two-Body's formula is exact (that is, the formula generates the known solution for a missile moving about a central body considering only the effect of the body viewed as a point mass) but is not an accurate model of a missile's actual force environment.

Valid values for {CoordinateType} are Cartesian, Classical, Equi, Spherical and MixedSpherical.

The {CoordSystem} parameter is case sensitive and must match the format used in the Trajectory page of the missile's Basic properties.

For valid {TimeInterval}, "<OrbitEpoch>" and "<CoordEpoch>" values see Time Options.

<StepSize> is entered in seconds.

The "<CoordEpoch>" parameter is only applicable, and is required, for a {CoordSystem} based on an Epoch, such as MeanOfEpoch, TrueOfEpoch, TEMEOfEpoch and AlignmentAtEpoch.

{CoordinateType}	<CoordTypeParameters>	<Description>
Cartesian	<X> <Y> <Z> <vX> <vY> <vZ>	<X>, <Y>, <Z>, <vX>, <vY> and <vZ> are entered using Connect distance units.
Classical	<SemimajorAxis> <Eccentricity> <Inclination> <ArgOfPerigee> <RAAN> <MeanAnom>	<SemimajorAxis> is entered using Connect distance units. <Inclination>, <ArgOfPerigee>, <RAAN> and <MeanAnom> are entered in degrees.
Equi	<SemimajorAxis> <h> <k> <p> <q> <MeanLon> {Retrograde \| Posigrade}	<SemimajorAxis> is entered using Connect distance units. <MeanLon> is entered in degrees.
MixedSpherical	<Longitude> <GeodeticLatitude> <Altitude> <HorizontalFlightPathAngle> <FlightPathAzimuth> <Velocity>	<Altitude> is entered using Connect distance units. <Longitude>, <GeodeticLatitude>, <HorizontalFlightPathAngle> and <FlightPathAzimuth> are entered in degrees. <Velocity> is entered using Connect distance units over Connect Time units
Spherical	<RightAscension> <Declination> <Radius> <HorizontalFlightPathAngle> <FlightPathAzimuth> <Velocity>	<Radius> is entered using Connect distance units. <RightAscension>, <Declination>, <HorizontalFlightPathAngle> and <FlightPathAzimuth> are entered in degrees. <Velocity> is entered using Connect distance units over Connect Time units

Examples

To set the trajectory of Missile using the TwoBody propagator, and the Classical element set:

SetUnits / km

SetState */Missile/Missile1 Classical TwoBody "1 Jun 2004 12:00:00.00" "1 Jun 2004 16:00:00.00" 5 J2000 "1 Jun 2004 12:00:00.00" 4582.24 0.8931 37.729 196.86 70.26 70.05

To set the trajectory of Missile using the TwoBody propagator, and the Spherical element set:

SetState */Missile/Missile4 Spherical TwoBody "1 Jun 2004 12:00:00.00" "1 Jun 2004 16:00:00.00" 5 J2000 "1 Jun 2004 12:00:00.00" 70.25 -0.0096 6378.14 60.73 52.27 6.16