MULTIPLICATIVE QUATERNION ERROR FEEDBACK FOR ORBITAL MANEUVERS

Quaternion parameterizations for the orientation of reference frames that are relevant to orbital motion are presented. The resultant dynamics are expressed in termsof these new coordinates which are then used to develop stabilizing feedback controllers. These controllers are unique to the application of spacecraft translational motion in that they utilize the composite rotation feature of the quaternion as opposed to the traditional additive state error. Furthermore, these coordinates avoid known singularities associated with Euler angles. An application of this feedback controller for a geocentric transfer is presented.