Halo Orbit Design Using Differential Correction

Script for creating "re-fined" initial conditions for Halo orbits in the Earth-Moon circular-restricted, three-body problem.

This MATLAB demonstrates halo orbit design in the Earth-Moon system using differential correction (dc). The code is "hard-wired" with the astrodynamic constants for the Earth-Moon circular-restricted, three-body problem and a Class I halo orbit about the L2 libration point.

script features

(1) initial guess using Richardson's algorithm

(2) solve system of nonlinear equations using fsolve

(3) graphics display of dc-refined halo orbit

The only input required from the user is the desired z-amplitude of the halo orbit in kilometers.