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.
   [qECIToBody, sAAngle, alpha, beta, yawRate, sARate] =
    QSunNadir( rECI, vECI, uSunECI, xNoSun, alphaLimit )

   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

   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



AerospaceUtils: Coord/QLVLH
Common: Graphics/Plot2D
Common: Quaternion/Mat2Q
Common: Quaternion/QMult
Common: Time/JD2000
Math: Linear/Cross
Math: Linear/Unit
SC: BasicOrbit/Period
SC: BasicOrbit/RVFromKepler
SC: Ephem/SunNadir
SC: Ephem/SunV1

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