Method for autonomously controlling the orbit of a satellite and autonomously controlled orbiting satellite

摘要

The orbit control method involves restoring values of position and speed using a calculation stage with corrective maneuvers provided by a navigator. The maneuvers take into account delay between command and actuation, minimum time between maneuvers, maximum authorized correction, correction consistence and authorized deviations. The data used includes modelled configurations, theoretical movements, error parameters, and constraints in maneuver computing. An Independent claim is included for a satellite controlled using the above method.