SATELLITE ORBIT CONFIGURATION METHOD, SATELLITE ATTITUDE CONTROL METHOD AND SATELLITE ORBIT SYSTEM

摘要

PROBLEM TO BE SOLVED: To solve a problem of a conventional satellite orbit configuration method correlating parameters required for a system employing a plurality of quasi-geostationary satellite orbits that has not yet been established.;SOLUTION: Number of apogee projection points and a required number of days for quasi-synchronization in a prime integer relation with the number of apogee projection points are decided, a satellite period of one circulation of a satellite on a quasi-geostationary satellite orbit is obtained based on the rotation period of the earth, the required number of days for quasi- synchronization and the number of apogee projection points, the adequacy of the orbit altitude of the satellite in a circulation motion for the satellite period is discriminated, and number of satellites is obtained based on the rotation period of the earth, the required number of days for quasi-synchronization and an operating time when the satellite serves a communication service.;COPYRIGHT: (C)2001,JPO