Determining the Optimal Trajectory For a Lunar Lander Using Modified Clohessy-Wiltshire Relative Motion Equations
Midshipman Researcher(s): 1/C Bradley Stephens
Adviser(s): CDR Jeffery T. King
Poster #3
The ability to land on the surface of the moon is a major focus of NASA in the coming future. With proposed missions like Artemis and Gateway, a minimum fuel trajectory for a lunar lander from lunar orbit to surface is crucial to advancement in space exploration. To determine the trajectory, an Optimal Control Problem (OCP) was defined using the Clohessy-Wiltshire (CW) relative motion equations. The CW equations were modified and rederived to remove traditional assumptions in order to make the solution to the OCP more robust.
