Path: SCPro/ProAttitude
% Build a constrained attitude profile consisting of multiple overlapping modes.
Each mode defines the ECI-to-Body quaternion through the combination of
primary and secondary alignments. The primary alignment directly aligns
a body vector with an inertial target. The secondary alginment rotates
about that primary body vector to align a second body vector with a
second inertial vector as closely as possible.
Each alignment can be defined as one of the following types, with the
associated target data.
# Alignment type Target data
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1 'sun' -
2 'nadir' -
3 'orbitnormal' -
4 'latlon' [lat;lon] Target latitude and longitude
5 'lvlh' [x;y;z] Target LVLH direction
6 'ueci' [x;y;z] Target ECI direction
7 'reci' [x;y;z] Target ECI point
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Form:
d = AttitudeProfileWithCon( d, mode1, mode2, mode3, ... );
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Inputs
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d (.) Data structure with orbit and time information
.jD0 (1,1) Epoch Julian date
.t (1,:) Time vector from jD0 (sec)
.r (3,:) ECI position (km)
.v (3,:) ECI velocity (km/s)
mode1 (.) Nominal Attitude Mode with fields:
.type1 '...' Primary alignment type
.body1 (3,1) Primary body vector to align
.target1 (:,1) Primary Target
.type2 '...' Secondary alignment type
.body2 (3,1) Secondary body vector to align
.target2 (:,1) Secondary target
.nCon (1,1)
.typeCon '...' Constraint type
.bodyCon (3,:,N)
.targetCon (3,N)
.minSepCon
mode2 (.) Same as nominal mode but with additional field:
.window (:,2) Time windows to use this mode
mode3
mode4
...
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Outputs
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d (.) Data structure with added quaternion, and alignment info
.jD0 (1,1) Epoch Julian date
.t (1,:) Time vector from jD0 (sec)
.r (3,:) ECI position (km)
.v (3,:) ECI velocity (km/s)
.el (1,6) Initial orbital elements
.q (4,:) ECI-to-body quaternion
.type1 (1,:) # for primary alignment type
.type2 (1,:) # for secondary alignment type
.rot (1,:) Rotation angle about primary body axis
.sep (1,:) Separation angle from secondary target
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See also: AttitudeProfileConstraintsDemo, AttitudeProfile, QAlignWithCon
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AerospaceUtils: Coord/ECIToEF AerospaceUtils: Coord/LLAToECEF AerospaceUtils: Coord/QAlign AerospaceUtils: Coord/QLVLH AerospaceUtils: Coord/QRotateToAlign AerospaceUtils: Coord/R2LatLon CubeSat: MissionPlanning/FindTimeWindows CubeSat: MissionPlanning/ObservationTimeWindows CubeSat: MissionPlanning/ObservationTimeWindowsPlot CubeSat: Utilities/LatLonPlot CubeSat: Utilities/WrapSegments Orbit: OrbitCoord/ENUToECEF Orbit: OrbitCoord/RAzToLatLon SC: BasicOrbit/E2M SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: BasicOrbit/OrbRate SC: BasicOrbit/RV2El SC: BasicOrbit/RVFromKepler SC: Ephem/MoonV1 SC: Ephem/SunV1 SCPro: ProAttitude/QAlignWithCon SCPro: ProAttitude/QRotateToAlignWithCon Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankAll Common: General/DeBlankLT Common: General/MatToCell Common: General/Watermark Common: Graphics/Axis3D Common: Graphics/Coordinates Common: Graphics/Ellipsd Common: Graphics/Map Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/Plot3D Common: Graphics/PlotAngleRange Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/TitleS Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Common: Quaternion/Mat2Q Common: Quaternion/QForm Common: Quaternion/QMult Common: Quaternion/QPose Common: Quaternion/QTForm Common: Quaternion/U2Q Common: Time/DTSToDTA Common: Time/Date2JD Common: Time/JD2000 Common: Time/JD2T Common: Time/T2JD Math: Geometry/AngleSepFromRotation Math: Geometry/FindValidAngleRange Math: Geometry/InsideAngleRange Math: Geometry/MergeAngleRange Math: Geometry/Perpendicular Math: Linear/Cross Math: Linear/Dot Math: Linear/DupVect Math: Linear/Mag Math: Linear/Unit Math: Trigonometry/CosD Math: Trigonometry/LinearSinCosToQuadCos Math: Trigonometry/SinD Math: Trigonometry/SolveLinearSinCos
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