Optimal trajectories towards near-earth-objects using solar electric propulsion (SEP) and gravity assisted maneuver

Abstract

Abstract:The solar electric propulsion could be the best option for the transports of the future due to its high specific impulse when compared to the chemical propulsion. Electric propellants are being extensively used to assist the propulsion of terrestrial satellites for the maneuvers of orbit correction and as primary propulsion in missions toward other bodies of the solar system. In this work the optimization of interplanetary missions using solar electric propulsion (SEP) and Gravity Assisted Maneuver to reduce the costs of the mission, is considered. The high specific impulse of electric propulsion makes a Gravity Assisted Maneuver 1 year after departure convenient. Missions for several Near Earth Asteroids will be considered. The analysis suggests criteria for the definition of initial solutions demanded for the process of optimization of trajectories. Trajectories to the asteroid 2002TC70 are analyzed. Direct trajectories, trajectories with 1 gravity assisted at the Earth and with 2 gravity assisted with the Earth and either Mars are presented. Shall be analyzed missions with thrusters PPS1350 and the Phall 1 for performance comparison. An indirect optimization method will be used in the simulations.

A numerical study of powered Swing-Bys around the Moon

“…In the next year, McConaghy et al (2003) combined Swing-By maneuvers with low thrust to obtain optimal trajectories. Combinations of low thrust and Swing-Bys are also shown in Okutsu et al (2006) and Santos et al (2008). Swenson et al (1992Swenson et al ( , 2006) studied missions to Neptune, while Prado and Felipe (2007) made a powered Swing-By analytical study.…”

Analytical study of the swing-by maneuver in an elliptical system

“…In a sequence, Casalino et al (1999a) expanded this analytical study to cover the situation where the impulse is applied in different points of the trajectory. There are several other works considering the study of the swing-by maneuver combined with an impulse in the spacecraft based on numerical integration (Prado 1997;Casalino et al 1999b;Santos et al 2008;Silva et al 2013;Ferreira et al 2015Ferreira et al , 2017aFerreira et al , 2017bFerreira et al , 2017cPiñeros and Prado 2017).…”

Analytical study of the powered Swing-By maneuver for elliptical systems and analysis of its efficiency

“…In this work the position of the application of the impulse is defined by the true anomaly of the spacecraft with respect to the secondary body. There are also several studies in the literature that combine low thrust, gravity assist and three body problem (Casalino et al 1999b;Mc-Conaghy et al 2003;Okutsu et al 2006;Santos et al 2008;Pourtakdoust and Sayanjali 2014;Zotos 2015;Qian et al 2016). Regarding practical applications, Flandro (1966) projected the Voyager missions, which were sent to explore the outer planets of the solar system.…”