Determining the Optimal Trajectory For a Lunar Lander Using Modified Equinoctial Elements
Midshipman Researcher(s): 1/C Julian Olivarez
Adviser(s): CDR Jeffery T. King
Poster #4
With renewed interest in returning to the Moon in the coming decade, it will be necessary to determine an optimal trajectory to minimize propellant expenditure for a lunar lander to land on the surface of the Moon from low lunar orbit. A common approach with low thrust orbital maneuvers is using a set of orbital elements known as the modified equinoctial elements to describe the motion. An optimal control problem was formulated to reduce the propellant mass consumed. The resulting dynamical data was then converted into the classical orbital elements to aid in spatial awareness.
