This MATLAB script demonstrates how to use modified equinoctial orbital element targeting to optimize two impulse orbital transfers subject to gravity perturbations. The script uses SNOPT to perform the optimization. An initial guess must be provided which can be obtained using the oota.m script included in my File Exchange suite of analysis tools. This script targets the semimajor axis, orbital eccentricity, orbital inclination, argument of perigee and right ascension of the ascending node of a user-defined elliptical mission orbit. It also displays a graphic representation of the orbital transfer. Several PDF documents are included in the archive.
Corrections and updates to PDF user's manual.
Added PDF user's manual