Reset attitude to use the attitude profile and offsets specified
SetAttitude <ObjectPath> Profile {ProfileType} <Parameters>
Use the SetAttitude Profile command to identify the orientation of the vehicle. Most attitude profiles are generated through the use of two vectors represented in the vehicle's body-fixed coordinate system, and two vectors represented in the inertial coordinate system. The first vector is referred to as the alignment vector; the second as the constraint vector.
Hint: If an axis is constrained, that particular axis attempts to point to the desired location as close as possible while still maintaining its proper relationship with the other axes defined in the coordinate system. When an axis is aligned, that axis points directly to the desired object, forcing the other axes to rotate accordingly.
Values for {ProfileType} are described in the table below. The Objects column indicates the specific vehicles for which a Profile type is valid. Ac = Aircraft, Gv = GroundVehicle, Lv = LaunchVehicle, Mi = Missile, Sa = Satellite, Sh = Ship
| {ProfileType} | <Parameters> | Objects | Profile Long Name |
|---|---|---|---|
| NadirECIVel | Offset <ConstrainOffset> | Sa, Lv, Mi | Nadir Alignment with ECI Velocity Constraint |
| NadirECFVel | Sa, Lv, Mi | Nadir Alignment with ECF Velocity Constraint | |
| NadirSun | Sa | Nadir Alignment with Sun Constraint | |
| NadirOrbit | Sa | Nadir Alignment with Orbit Normal Constraint | |
| ECIVelNadir | Sa, Lv, Mi, Ac, Gv, Sh | ECI Velocity Alignment with Nadir Constraint | |
| ECFVelNadir | Sa, Lv, Mi, Ac, Gv, Sh | ECF Velocity Alignment with Nadir Constraint | |
| ECFVelRadial | Sa, Lv, Mi, Ac, Gv, Sh | ECF Velocity Alignment with Radial Constraint | |
| NorthEastDown | Sa, Lv, Mi, Ac, Gv, Sh | Nadir alignment with North constraint | |
| SunNadir | Offset <AlignOffset> | Sa, Mi | Sun Alignment with Nadir Constraint |
| SunEcliptic | Sa | Sun Alignment with Ecliptic Normal Constraint | |
| SunECIZ | Sa | Sun Alignment with ECI Z Axis Constraint | |
| SunOccult | Sa | Sun Alignment with Occultation Normal Constraint | |
| CBIVelSun | Sa, Mi | ECI Velocity Alignment with Sun Constraint | |
| SunPointingZOrbit | Sa, Mi | Sun Alignment with Z in Orbit Plane | |
| XPOPInertial | Sa | XPOP Inertial | |
| YawNadir | {OrientMethod} <OrientParameters> | Sa | Yaw to Nadir |
| AlignConstrain | {AlignOrientMethod} <AlignOrientParams> "<AlignRefVector>" {CnstrOrientMethod} <CnstrOrientParams> "<CnstrRefVector>" | Sa, Lv, Mi, Ac, Gv, Sh | Aligned and Constrained |
| SpinAlignCrdn | {BodyOrientMethod} <BodyOrientParams> "<RefVector>" <PrecessingRate> <PrecessingOffset> <SpinRate> <SpinOffset> <NutAngle> {EpochTime} | Sa, Lv, Mi | Spin Aligned |
| Spinning | Inertial {OrientMethod} <OrientParameters> Body {OrientMethod} <OrientParameters> <SpinRate> <SpinOffset> {EpochTime} | Sa, Lv, Mi | Spinning |
| SpinNadir | <SpinRate> <SpinOffset> {EpochTime} | Sa | Spin about Nadir |
| SpinSun | Sa | Spin about Sun Vector | |
| PrecessingSpin | Inertial {OrientMethod}<OrientParameters> Body {OrientMethod} <OrientParameters> <SpinRate> <PrecessionRate> <NutationAngle> <SpinOffset> <PrecessionOffset> {EpochTime} ["<ReferenceFrame>"] | Sa, Lv, Mi | Precessing Spin |
| InertFix | {OrientMethod} <OrientParameters> | Sa, Mi | Inertially Fixed |
| Fixed | {OrientMethod} <OrientParameters> ["<RefAxes>"] | Sa, Lv, Mi, Ac, Gv, Sh | Fixed in Axes |
| AircraftCoordTurn | [<TimeOffset>] | Ac | Coordinated Turn |
| GPS | ModelType {IIANominal | IIFNominal | IIRNominal | IIA | IIF | IIR | QZSS | GalileoIOV} | Sa | GPS |
For the Fixed {ProfileType} the "<RefAxes>" can not be the object's Body Axes.
For valid {EpochTime} values see Time Options.
<ConstrainOffset>, <AlignOffset>, <SpinOffset>, <RAAN>, <Declination>, <Yaw>, <Pitch>, <Roll>,<Euler1>, <Euler2> and <Euler3> are entered in degrees.
When using the AlignConstrain, SpinAlignCrdn and Fixed {ProfileTypes}, use the formats outline in the following Table for specifying axes and/or vectors:
| Specify an axes/vector of: | Format | Example |
|---|---|---|
| Current Vehicle | Indicate the name of the axes/vector in quotes. | "LVLH" or "OrbitMomentum" |
| Central Body | Indicate the truncated path of the central body followed by a space and the axes/vector name, all in quotes. | "CentralBody/Earth Inertial" or "CentralBody/Earth Moon" |
| Other Objects | Indicate the truncated path of the object followed by a space and the axes/vector name, all in quotes. | "Satellite/attSat Ecc" or "Facility/Facility1 RadialCentric" |
Hint: The current vehicle is specified by the <ObjectPath> in the command.
When using the <YawNadir>, <AlignConstrain>, <SpinAlignCrdn>, <Spinning> and <PrecessingSpin> {ProfileTypes}, {OrientMethod}, {AlignOrientMethod}, {CnstrOrientMethod} and {BodyOrientMethod} can be:
| {Align | Cnstr | BodyOrientMethod} | <OrientParameters> |
|---|---|
| PR | <Pitch> <Roll> |
| Euler | <Angle1> <Angle2> <Sequence>, where <Sequence> can be <12>, <21>, <31> or <32> |
| RaDec | <RAAN> <Declination> |
| Axis | <x> <y> <z> |
When using the <InertFix> and <Fixed> {ProfileTpes}, {OrientMethod} can be:
| {Align | Cnstr | BodyOrientMethod} | <OrientParameters> |
|---|---|
| YPR | <Yaw> <Pitch> <Roll> <Sequence>, where <Sequence> can be <RPY>, <RYP>, <PRY>, <PYR>, <YRP> and <YPR> |
| Euler | <Angle1> <Angle2> <Angle3> <Sequence>, where <Sequence> can be <121>, <123>, <131>, <132>, <212>, <213>, <231>, <232>, <312>, <313>, <321> and <323> |
| Quat | <Q1> <Q2> <Q3> <Q4> |
To set the attitude profile to Fixed type with a vector of type Euler and a reference axes of CentralBody/Earth B1950:
SetAttitude */Satellite/aosSat Profile Fixed Euler 11 22 33 313 "CentralBody/Earth B1950"
SetAttitude */Satellite/aosSat Profile AlignConstrain PR 90.0 0.0 "GrvGrdTorque" Axis 0 0 1 "Satellite/attSat Sun"
SetAttitude */Satellite/aosSat Profile SpinAlignCrdn RaDec 10.0 88.0 "Facility/aosFac North" 1.2 0.01 2.4 0.0 22.4 "1 Jan 2001 00:00:00.00"
To set the attitude of the Shuttle so that its default attitude type is inertially fixed, with a Euler angles orientation method, and 11.1 22.1 33.1 values to be executed as 313:
SetAttitude */Satellite/Shuttle Profile InertFix Euler 11.1 22.1 33.1 313
To set the shuttle's attitude so that it spins about its Z body axis:
SetAttitude */Satellite/Shuttle Profile Spinning Inertial PR 10.0 20.0 Body axis 0.0 0.0 1.0 1.8 12.0 "1 Feb 2000 00:00:00.00"
To set a Precessing spin attitude, first without, then with a ReferenceFrame:
SetAttitude */Satellite/BasicSat1 Profile PrecessingSpin Inertial PR 0.0 12.0 Body PR 0.05 10.0 2.5 0.5 32.0 0.0 0.0 "1 Jan 2001 00:00:00.00"
SetAttitude */Satellite/BasicSat1 Profile PrecessingSpin Inertial PR 0.0 12.0 Body PR 0.05 10.0 2.5 0.5 32.0 0.0 0.0 "1 Jan 2001 00:00:00.00" "Satellite/Satellite1 J2000"
This command belongs to the following group(s):
11
STK Programming Interface 11.0.1