Path: Missions/SunNadir
% Initial quaternion and solar array angle given the sun geometry. Given an inertial frame defined with the sun in the +ZY plane, compute the initial spacecraft quaternion and solar array angle given the sun beta angle and alpha, the angle between the spacecraft and the sun projection in the ZX plane. -------------------------------------------------------------------------- Form: [q, sAAngle, w] = ICSN( xNoSun, orbitRate, beta, alpha, alphaLimit ) -------------------------------------------------------------------------- ------ Inputs ------ xNoSun (1,1) Either +1 for +x or -1 for -x orbitRate (1,1) Orbit rate beta (1,1) Angle from orbit plane to the sun (rad) alpha (1,1) Angle from the sun line in the orbit plane alphaLimit (1,1) Range of alpha during which the rate limit is to be enforced ------- Outputs ------- q (4,1) Quaternion saAngle (1,1) Solar array angle w (3,1) Body rate -------------------------------------------------------------------------- See also SunNadir. --------------------------------------------------------------------------
SC: Ephem/SunNadir Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Quaternion/Mat2Q
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