Optimal aeroassisted orbital plane change subject to G constraint

The optimal aeroassisted orbital plane change trajectories subject to G constraint is considered. To overcome the highly numerical sensitivity of the equations of motion and the adjoint equations, the continuation method is used to express Newton's iteration divergence, and the multiple shooting technique is used to depress the integration divergence. The G constraint penalty pertaining to orbital plane change angle and exit flight path angle is small, but the flight time in the constrained case is found to be much longer than in the unconstrained one.