Spacecraft Attitude Determination Using Global Positioning Satellite Signals



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(7.2)

(7.3)

For which is the rotational acceleration of the spacecraft about the x axis, is the rotational rate about the x axis, and is the moment of inertia about the x axis.

The orbital propagator performs calculations in the PQW coordinate frame. The local orbital frame will be the quasi-inertial coordinate frame used for calculations:



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