Abstract:
The one impulse return trajectory from Moon orbit is considered. The right point of the return trajectory is entry point to Earth atmosphere. The purpose of considered method is to calculate optimal impulse that ensures limitations in right point of the trajectory. These limitations must provide landing of reentry vehicle in specified area of Earth surface. Several tasks with different sets of limitations are considered. The results of mathematic simulation for several Moon orbits are presented.
Keywords:satellite of the Moon, transfer trajectory from Moon to Earth, numerical method, conditional minimization.
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