Path: SC/Dynamics
% Right-hand-side for spacecraft attitude and orbit with a gyro. Angular rate is an input. Point mass orbit model. -------------------------------------------------------------------------- Form: d = RHSGyroWithOrbit; % To get the data structure xDot = RHSGyroWithOrbit( x, t, d ) -------------------------------------------------------------------------- ------ Inputs ------ x (16,1) State vector [r;v;q;imuAng;imuBias] t (1,1) Time (unused) d (.) Data structure .mu (1,1) Gravitational constant .b1Sig (1,1) Bias random walk .ang1Sig (1,1) Angle noise .omega (3,1) Angular rate ------- Outputs ------- xDot (16,1) State vector derivative d[r;v;q;imuAng;imuBias]/dt --------------------------------------------------------------------------
AerospaceUtils: Coord/QIToBDot Math: Linear/Mag
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