Path: SpacecraftEstimation/StellarAttDet
% Quaternion derivative. ------------------------------------------------------------------------ Form: dQ = RHSQ( qECIToBody, t, omega ) ------------------------------------------------------------------------ ------ Inputs ------ qECIToBody (4,1) Quaternion from the ECI to body frame t (1,1) Time (sec) omega (3,1) Angular rate (rad/sec) ------- Outputs ------- dQ (4,1) Quaternion derivative ------------------------------------------------------------------------
AerospaceUtils: Coord/QIToBDot Common: Control/C2DZOH Math: Linear/SkewSymm
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