A simple and efficient method using the fireworks algorithm (FWA) is presented for pruning the search space of an impulsive maneuver transfer from a user-defined low Earth orbit (LEO) to a desired lunar halo orbit around Earth– moon Lagrange point 2. The dynamical framework adopted is the circular restricted three-body problem. The FWA method is used to optimize both the two-burn direct impulsive transfer and the impulsive transfer that uses stable manifolds. Sample LEO to lunar halo trajectories, along with their required ΔV costs and times of flight (TOFs), are provided and compared to known numerical techniques. The results obtained are close in both ΔV and TOFs to what the existing literature reports, which demonstrates the validity of the proposed method.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Space and Planetary Science