Bachelor’s project: Low energy trajectories to the moon

Bachelor's project front page

A new design strategy for finding low energy trajectories from Earth orbit to Moon orbit through the first Lagrange point has been developed. The found trajectories are very close to the theoretical minimum values of v necessary to go from Earth orbit to L1 and from L1 to Moon orbit. However, a large velocity change at L1 gives the most fuel effective trajectory a total vof 4369.5 m/s.

As part of the project, seven different one step integrators have been compared, with six of these being symplectic integrators. It was found that the integrator, which approximated the flow of the restricted three body system the fastest and most accurately, was the non-symplectic 4th order Runge-Kutta Method.

You can download the project here.