SetAttitude Profile
Reset attitude to use the attitude profile and offsets specified
Syntax
SetAttitude <ObjectPath> Profile {ProfileType} <Parameters>
Related commands
Description
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.
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>" cannot be the object's Body Axes.
For valid {EpochTime} values, see Time Options.
Enter <ConstrainOffset>, <AlignOffset>, <SpinOffset>, <RAAN>, <Declination>, <Yaw>, <Pitch>, <Roll>,<Euler1>, <Euler2>, and <Euler3> in degrees.
When using AlignConstrain, SpinAlignCrdn, and Fixed {ProfileTypes}, use the formats outline in the following table for specifying axes or vectors or both:
| 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" |
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>
Similarly to Euler angles, YPR angles specify attitude using three rotations in a chosen sequence: the rotation about the reference X axis is called roll (R), the rotation about the reference Y axis is called pitch (P), and the rotation about the reference Z axis is called yaw (Y). Sequences are identified using either numbers (1 is the X axis, 2 is the Y axis, 3 is the Z axis) or letters (R is the X axis, P is the Y axis, Y is the Z axis). Unlike Euler angles, the rotations are not made about axes defined by an earlier rotation. Instead, each rotation is made about the reference system's axes. In YPR angles, the names yaw, pitch, and roll do NOT refer to the angles normally used in aviation; the terms yaw, pitch, and roll in aviation refer to 321 Euler angles. |
| Euler | <Angle1> <Angle2> <Angle3> <Sequence>, where <Sequence> can be <121>, <123>, <131>, <132>, <212>, <213>, <231>, <232>, <312>, <313>, <321>, or <323> |
| Quat | <Q1> <Q2> <Q3> <Q4> |
Examples
To set the attitude profile to Fixed type with a vector of type Euler and a reference axes of CentralBody/Earth B1950:
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:
To set the shuttle's attitude so that it spins about its Z body axis:
To set a Precessing spin attitude, first without, then with a ReferenceFrame:
Return message
If activated, Connect returns an acknowledgement message.Group membership
This command belongs to the following group(s):
Version
11