کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
1714406 | 1519944 | 2015 | 14 صفحه PDF | دانلود رایگان |

• Optimal transfer trajectory to Halo orbit using the four body model.
• Pseudo-invariant manifolds are utilized for low energy transfers.
• Trajectory optimization via a hybrid approach.
• Design variables include Moon angle, Halo orbit points and different thrust cut offs.
This paper investigates the problem of optimal transfer trajectory design towards the L2 centered Halo orbit of the Sun–Earth three body system, where the initial launch is to start from a low Earth parking orbit (LEO). The proposed optimal transfer trajectory consists of an active part with low-thrust propulsion and a passive coasting part with no thrust or fuel consumption. In this respect a pseudo-stable manifold (SM) is initially determined through backward time integration of the bicircular four body (BCFB) equations of motion, whose initial states are obtained via stable manifolds of the restricted three body problem (R3BP). The optimal transfer trajectories are extracted via a hybrid direct–indirect optimization formulation applied on both R3BP as well as the BCFB models for comparative purposes. The optimal transfer trajectories are designed and analyzed for different Halo injection points (HOI), different Moon׳s final anomaly (FMA) and also for different locations of the burn-out conditions.
Journal: Acta Astronautica - Volume 110, May–June 2015, Pages 115–128