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To design the optimal lunar landing trajectory, the periapsis of de-orbit burn phase is usually used as a starting point of the powered descent phase. And the optimal problem is constructed based on the initial states at this point. For this optimal problem, some kinds of result trajectories have the increase in their own altitude at the early stage to earn the enough time to reduce their huge horizontal...
In this research, the trajectory correction maneuver(TCM) is proposed for the spacecraft has an interplanetary mission with low-thruster such as electric propulsion system. During the trasfer phase of the interplanetary mission, the trajectory error occurs due to the influence of external perturbation forces. Thus, the TCM is required to reduce this error. In the previous researches, the TCM techniques...
A lunar orbital capture guidance law is presented for a spacecraft with electrical propulsion system using Lyapunov feedback control approach. Construction of the Lyapunov function candidate is based on orbital elements which consist of angular momentum and eccentricity vectors. Unlike the orbit transfer problem between closed orbits, the lunar capture problem has two constraints. One thing is that...
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