Optimization of three-impulse, low-energy Earth-Moon transfer trajectories with a fixed time of flight in the restricted four-body problem is investigated in this work. Based on the two-impulse, low-energy solutions, a strategy is developed to design the time-fixed optimal three-impulse Earth-Moon transfers. The necessary conditions of optimality for a two-impulse transfer are stated in terms of the primer vector. Primer vector theory is then extended to nonoptimal two-impulse trajectories to establish a criterion whereby adding an interior impulse reduces total fuel expenditure. Examples of optimal three-impulse, low-energy Earth-Moon transfer trajectories are presented. The differences between the two-impulse transfers and three-impulse transfers are discussed.

On Optimal Three-Impulse Earth-Moon Transfers in a Four-Body Model

Topputo, F.;Wang, Y.
2022-01-01

Abstract

Optimization of three-impulse, low-energy Earth-Moon transfer trajectories with a fixed time of flight in the restricted four-body problem is investigated in this work. Based on the two-impulse, low-energy solutions, a strategy is developed to design the time-fixed optimal three-impulse Earth-Moon transfers. The necessary conditions of optimality for a two-impulse transfer are stated in terms of the primer vector. Primer vector theory is then extended to nonoptimal two-impulse trajectories to establish a criterion whereby adding an interior impulse reduces total fuel expenditure. Examples of optimal three-impulse, low-energy Earth-Moon transfer trajectories are presented. The differences between the two-impulse transfers and three-impulse transfers are discussed.
2022
73rd International Astronautical Congress (IAC 2022)
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11311/1221300
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