Design of multi-revolution orbits in the framework of elliptic restricted three-body problem using differential evolution

Abstract

In the elliptic restricted three-body problem framework, periodic orbits are multi-revolution (MR) orbits. In the conventional approach to design an MR orbit, the circular halo orbit initial conditions are used with continuation on eccentricity and by dividing the whole orbit into multiple segments. An alternative scheme based on differential evolution is developed which avoids the continuation on eccentricity and treats the whole trajectory (MR orbit) as a single segment. The design and analysis of different MR orbits in the Sun–Earth system are presented. Unlike in the differential correction based method, the proposed methodology could produce both Lyapunov and halo orbit MR solutions for the same period. Further, it could capture multiple solutions for each of the halo or Lyapunov MR orbits. Multithreading technique has been employed to reduce the computational time.