Trajectory Optimization Using Nonsingular Orbital Elements and True Longitude

The system and adjoint differential equations needed to solve low-thrust transfer and rendezvous trajectories are derived in terms of nonsingular orbit elements, with the true longitude selected as the sixth variable that also dee nes the radial distance. The perturbation accelerations are resolved in the rotating polar frame such that the equations of motion are written in polarcoordinates. This formulation is particularly convenient forthe treatment of the J2 perturbation acceleration whose components are easily expressed in terms of the true longitude. The iterations needed for the solution of Kepler’ s equation are also eliminated, and the analytic form of the adjoint equations is provided in their simplest aspect thus far.