Optimal low-thrust transfers between libration point orbits

Abstract

Over the past three decades, ballistic and impulsive trajectories between libration\ud point orbits (LPOs) in the Sun–Earth–Moon system have been investigated to a large extent.\ud It is known that coupling invariant manifolds of LPOs of two different circular restricted\ud three-body problems (i.e., the Sun–Earth and the Earth–Moon systems) can lead to significant\ud mass savings in specific transfers, such as from a low Earth orbit to the Moon’s vicinity.\ud Previous investigations on this issuemainly considered the use of impulsive maneuvers along\ud the trajectory. Here we investigate the dynamical effects of replacing impulsive V’s with\ud low-thrust trajectory arcs to connect LPOs using invariant manifold dynamics. Our investigation\ud shows that the use of low-thrust propulsion in a particular phase of the transfer and the\ud adoption of a more realistic Sun–Earth–Moon four-body model can provide better and more\ud propellant-efficient solution. For this purpose, methods have been developed to compute the\ud invariant tori and their manifolds in this dynamical modelPeer ReviewedPostprint (published version

Optimization of low-thrust transfers to libration point orbits

“…Hence, comparing with the impulsive transfer, low-thrust transfer by using solar electric propulsion is a more economic choice for this kind of mission. The low-thrust transfers from the LEO to LPOs were investigated by several researchers (Sukhanov and Eismont, 2003;Masdemont, 2005;Starchville and Melton, 1998;Armellin and Topputo, 2006;Mingotti et al, 2011;Ren et al, 2012). The results of these existing research works have shown that significant payload advantages of low-thrust propulsion for orbit transfers are possible.…”