The low-thrust version of the low energy transfers to the Moon exploiting the structure of the invariant manifolds associated to the Lagrange point orbits is presented in this paper. A method to systematically produce low-energy, low-thrust transfers executing ballistic lunar capture is discussed. The coupled restricted three-body problems approximation is used to deliver appropriate first guess for the subsequent optimization of the transfer trajectory within a complete four-body model using direct transcription and multiple shooting strategy. It is shown that less propellant than standard low energy transfers to the Moon is required. This paper follows previous works by the same authors aimed at integrating together knowledge coming from dynamical system theory and optimal control problems for the design of efficient low-energy, low-thrust transfers
In this paper we incorporate the low-thrust propulsion in the stable manifold technique to design transfer trajectories to the halo orbits around L 1 and L 2 of the Earth-Moon system. The problem is stated in an optimal control scheme and solved using direct transcription and collocation; the dynamics is discretized over an uniform time grid using a sixth-order linear multi-point method. The resulting transfers are made up by a spiral arc that targets a piece of the stable manifold associated to the final orbit. Thanks to the generality of this approach, halo-to-Moon transfers are also computed combining unstable manifolds and low-thrust. Furthermore, complete Earth-to-Moon transfers via halos can also be constructed. Results show the feasibility of this kind of transfers requiring moderate propellant mass fractions and feasible times of flight.
A method to incorporate low-thrust propulsion into the invariant manifolds technique is presented in this paper. The low-thrust propulsion is introduced by means of special attainable sets that are used in conjunction with invariant manifolds to define a first-guess solution. This is later optimized in a more refined model where an optimal control formalism is used. Planar low-energy low-thrust transfers to the moon, as well as spatial low-thrust stable-manifold transfers to halo orbits in the Earth moon system, are presented. These solutions are not achievable via patched-conics methods or standard invariant manifolds techniques. The aim of the work is to demonstrate the usefulness of the proposed method in delivering efficient solutions, which are compared with known examples
In this paper novel Earth-Mars transfers are presented. These transfers exploit the natural dynamics of n-body models as well as the high specific impulse typical of low-thrust systems. The Moon-perturbed version of the Sun-Earth problem is introduced to design ballistic escape orbits performing lunar gravity assists. The ballistic capture is designed in the Sun-Mars system where special attainable sets are defined and used to handle the low-thrust control. The complete trajectory is optimized in the full n-body problem which takes into account planets' orbital inclinations and eccentricities. Accurate, efficient solutions with reasonable flight times are presented and compared with known results.
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