Manobras orbitais aplicadas aos problemas de dois e tres corpos

AUTOR(ES)
DATA DE PUBLICAÇÃO

2000

RESUMO

In the space activities, it is of great importance the study of the trajectories that the space vehicles should follow to complete a mission. With that motivation, the present research is concentrated in the study of those trajectories, under the dynamics given by: a)The traditional Problem of Two Bodies with Keplerian orbits where the space vehicle is supposed to move around a heavenly body modeled by a point of mass; b)The wellknown Restricted Problem of Three Bodies Model, where the space vehicle is assumed as being a point of mass that moves due to the gravitational forces of two primaries, that are two heavenly bodies modeled as point of mass and that are in Keplerian orbits around a common center of mass. Maneuvers accomplished with the use of engines capable to supply instantaneous variations of velocity in a space vehicle and maneuver that use only gravitational forces will be studied. Comparisons among different options for the respective maneuvers will be made. The maneuvers that requires that two spacecrafts encounter in the space (Rendezvous)are also considered, as well as maneuvers considering constellations of satellites.

ASSUNTO(S)

engenharia e tecnologia espacial trajetorias trajectories tree body problem astrodynamics mecanica celeste two body problem spacecrafts orbits orbita de satelites astrodinamica problema de tres corpos transferencia orbital problema de dois corpos celestial mechanics

ACESSO AO ARTIGO

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