A system and method (30, 50) for correcting pointing errors induced by an inclined orbit (14) for a satellite (20) that is adapted to be in an orbit (12) having zero inclination. The present invention generates (34) a yaw correcting cosine rate command that is integrated (36) by a steering law having input parameters dependent upon the angle (Θ) of inclination to derive (38) a sinusoidal yaw offset. The present invention also generates (54) a roll correcting cosine rate command that is integrated (56) according to a steering law having input parameters dependent upon the angle (Θ) of inclination to derive a sinusoidal roll offset (Fig. 4).
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