Path: SC/Ephem
% Compute the sun-nadir quaternion and other quantities.
If less than three inputs are given, it will run a demo for a GPS orbit.
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Form:
[qECIToBody, sAAngle, alpha, beta, yawRate, sARate] =
QSunNadir( rECI, vECI, uSunECI, xNoSun, alphaLimit )
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Inputs
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rECI (3,:) Spacecraft position in ECI frame
vECI (3,:) Spacecraft velocity in ECI frame
uSunECI (3,:) Sun position in ECI frame
xNoSun (1,1) Either +1 for +x or -1 for -x
alphaLimit (1,1) Range of alpha within which the rate limit is to
be enforced
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Outputs
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qECIToBody (4,:) Quaternion from ECI to body
saAngle (1,:) Solar array angle
alpha (1,:) Angle from the sun line in the orbit plane
beta (1,:) Beta angle
yawRate (1,:) Yaw rate
sARate (1,:) Solar array rate
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AerospaceUtils: Coord/QLVLH SC: BasicOrbit/E2M SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: BasicOrbit/Period SC: BasicOrbit/RV2El SC: BasicOrbit/RVFromKepler SC: Ephem/SunNadir SC: Ephem/SunV1 Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/Plot3D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Common: Quaternion/Mat2Q Common: Quaternion/QMult Common: Time/DTSToDTA Common: Time/Date2JD Common: Time/JD2000 Math: Linear/Cross Math: Linear/DupVect Math: Linear/Mag Math: Linear/Unit Math: Trigonometry/CosD Math: Trigonometry/SinD
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