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