Minimum Time Orbit Raising of Geostationary Spacecraft by Optimizing Feedback Gain of Steering Law

Abstract

This study considers the minimum time orbit-raising problem of geostationary spacecraft with low-propulsion thrusters. This problem is equivalent to determining an appropriate thrust direction during orbit raising. This study proposes a closedloop thruster steering law that determines the thrust direction based on the optimal feedback gains and control errors of each orbital element. The feedback gains of the steering law are assumed to be the functions of orbital elements and are optimized by a meta-heuristic method. The orbital semi-major axis, eccentricity, and inclination are considered as independent variables for expressing the gains. Numerical simulations show that whichever orbital elements is selected as an independent variable, the same performances are obtained. Therefore, regardless of the initial orbital elements, by selecting the independent variable appropriately, the proposed method can always solve the minimum time orbit-transfer problem.

A Concept Study of the All-Electric Satellite’s Attitude and Orbit Control System in Orbit Raising

“…For example, the Sequential quadratic programming (SQP) method [7] and Particle swarm optimization method [8] have been proposed to optimize the transfer time. These solutions require complicated orbit and attitude control, but few studies have demonstrated an acceptable method of attitude control.…”