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.

在椭圆约束三体问题框架中，周期轨道是多旋转（MR）轨道。在设计MR轨道的常规方法中，使用圆形光晕轨道初始条件并保持偏心率不变，并将整个轨道分为多个部分。提出了一种基于差分演化的替代方案，该方案避免了偏心率的延续，并将整个轨迹（MR轨道）视为单个片段。介绍了太阳-地球系统中不同MR轨道的设计和分析。与基于差分校正的方法不同，所提出的方法可以同时产生Lyapunov和晕轨道MR解决方案。此外，它可以为每个晕圈或Lyapunov MR轨道捕获多种解决方案。