Large-Angle Kinematics for the Control of Satellite Relative Motion
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Relative motion between satellites is viewed on a unit sphere on which distances are equivalent to direction cosines. The inter satellite range vector is expressed in terms of Euler parameters. Relative angular velocity vector and orientation of one satellite with respect to another are also derived using the differences in the respective orbital elements and their rates. The required rates of the mean element differences are determined using various kinematic control laws for formation maintenance as well as reconfiguration. The solutions for the required differences in the rates of the orbital elements are not unique and are strongly influenced by the time of initiation of the control action as related to the position of the controlled satellite in its orbit. © 2002 by the author(s). Published by the American Institute of Aeronautics and Astronautics, Inc.
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