Abstract
Abstract : Low-thrust maneuvers are evaluated by calculating changes in the orbital elements with pre-defined steering programs. Four pitch steering cases are considered, where the in-plane acceleration vector is (1) perpendicular to the orbit radius vector, (2) tangent to the orbit path, (3) perpendicular to the major axis of the ellipse, and (4) parallel to the major axis of the ellipse. Discontinuous thrusting is described using perigee- and apogee-centered burn arcs. Expressions are given for the secular rates of change of the orbital elements, which can be integrated numerically or in some instances solved in closed form to yield the AV and trip time. Maneuvers analyzed here include simultaneous eccentricity and inclination changes, adjusting the argument of perigee and right ascension of the ascending node (RAAN), phase shifting with RAAN control, and changes of the semimajor axis and eccentricity due to atmospheric drag. Mission applications are illustrated by orbit insertion at low, medium, and geosynchronous altitudes using chemical and electric propulsion, orbit disposal by re-entry or grave yarding, and controlling the separation distance between a target and a chase satellite in low Earth orbit.
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