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.

Full Size Aerospace Engineering #1