In this paper, the concept of a simple attitude control method that achieves orbit-raising time optimization and has little design effect on the subsystem, except for on the electric propulsion subsystem, is reported. | Journal of Automation and Control Engineering Vol. 5, No. 2, December 2017 A Concept Study of the All-Electric Satellite’s Attitude and Orbit Control System in Orbit Raising Yoshinobu Sasaki Japan Aerospace Exploration Agency / Space Technology Directorate I, Tsukuba-city, Ibaraki, Japan Email: Fig. 1 compares the simulation result for the satellite mass ratio (drymass/propellant) for a conventional satellite and an electric satellite. It is assumed that the satellite mass (BOL) is 5000 kg, that the propellant used is for GTO to GEO transferring, and that out-of-plane control is in GEO. Abstract—All-electric satellite systems and electric propulsion are becoming increasingly well-known technologies, because they help in reducing the propellant weight by a significant amount and enable the mounting of an increased mission payload. Unfortunately, the systems suffer from a much longer Geostationary transfer orbit (GTO) to Geostationary equatorial orbit (GEO) transfer time. This means there is more delay inimp service-in times. Since the transfer orbit is in the Van Allen radiation belt, it is advisable to shorten the transfer time. To resolve this problem, significant progress has already been made to optimize the orbit and attitude control. These solutions require complex orbits and attitude control; relatively little research has studied the attitude control method. In this paper, the concept of a simple attitude control method that achieves orbit-raising time optimization and has little design effect on the subsystem, except for on the electric propulsion subsystem, is reported. 7000 Total Propellant Satellite Mass (Wet) [kg] 6000 Index Terms—All-Electric Satellite, GTO, GEO, OrbitRaising, Attitude Control, Electric Propulsion Satellite Mass (Dry) 5000 4000 Propellant Reduction 3000 2000 1000 I. INTRODUCTION 0 Geostationary satellites have conventionally used a two-liquid propulsion system for transferring themselves from .
