Sharif Digital Repository

Optimal Maneuvering to lessen the required fuel or to speed up the mission operation time is a significant part of various space missions. Optimal performance of a spacecraft reduces the mission cost, increases the mission life time and subsequently provides more chances for space exploration. In this sense, optimal maneuvering has always been at the center of attention and abundant works have been assigned to this importance. This research is also devoted to optimal trajectory design to transfer from low Earth orbits to the halo orbits. Specific characteristics of the halo orbits including periodicity, geometry, and particular position around the collinear liberation points of the... 

The subject of low thrust transfer trajectory design to the Sun-Earth L2 Lagrange point, considering the Moon’s gravitational attraction as the fourth body effect has been investigated. In addition, three body resonance orbits chaotic dynamics are also studied. The problem of transfer trajectory design to Earth-Moon halo orbit is investigated using two approaches for the thrusting phase of flight.In the first approach, a complete Bicircular four body model is utilized to initially insert an Earth bound spacecraft via active low thrust propulsion on a stable manifold (SM) of the Earth-Moon three body system. Subsequently, the spacecraft coasts to its desired Halo orbit with minimum Trajectory...