Results of orbital maneuvers by an observational satellite

The linearized theory of optimal orbit corrections, i.e., minimization of the characteristic velocity, is used to model various orbital maneuvers for a remote sensing satellite. Specific calculations are made for positioning the spacecraft for a survey orbit, for flying over a specific point once or repeatedly, and for transfer into a sunsynchronous, maximum height, safeguard orbit. The studies are made to optimize the maneuvers in terms of injection errors minimization and orbital perturbations compensation. Minimizing the constant velocity leads to fuel optimization, and linearity is maintained by considering orbits only slightly different from the orbit of injection. Repeated overflights and changes of direction to a specific point are noted to be possible with either circular or elliptical orbits, and are performed through in-plane or out-of-plane maneuvers. Overflights above sites other than on the equator are examined, as are instances for the beginning and end of maneuvers, and for intermittent thrust impulses.