RHSQ:

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 

------------------------------------------------------------------------

Children:

AerospaceUtils: Coord/QIToBDot

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