Dynamics of artificial satellites

Abstract

The objective of this work is to continue the study of models and methods used for the calculation of optimal space trajectories, from the point of view of lower fuel consumption, for a transfer of a spacecraft between two given orbits. We will study various options for modeling the dynamic action of the actuators and methods of optimization. Classical methods (Hohmann transfer, bi - elliptical, etc.) and modern methods (involving gravitational capture, gravity assist maneuvers and "tethers") will be searched. This is a continuation of the research work that the proponent has developed during his master's thesis at the National Institute for Space Research - INPE (Brazil, 1987-1989 ); specialization at the International Space University (France, 1989); doctorate from the University Texas (USA, 1990-1993), as a professor in the graduate school in Space Mechanics and Control at the National Institute for Space Research - INPE (Brazil, 1994 - present), as a researcher from CNPq PQ (since August 1995 to the present, currently at level 1A), within a project "Jovem Pesquisador" from FAPESP between June 1996 and June 2000 and several regular research projects FAPESP in the past 13 years. The goals of this research work wants to achieve are several. The main one is to conduct further research to generalize and/or extend existing results and, especially, the development of new methods. In this task the researcher's proponent, many graduate students (masters and doctorate levels), postdoctoral and undergraduate research are already involved, in addition to new students who will be included in next two years. (AU)