A method is presented for selecting initial values for orbital parameters that permit larger intervals in the numerical integration of low-thrust planet-escape trajectories. The results are derived for cases where the only acceleration causing non-two-body motion is due to a propulsion device having a constant propellant-flow rate and thrust alined in either the circumferential or tangential direction. Also, it is demonstrated that the results may be extended to thrust programs that are slightly off either the tangential or circumferential direction.
展开▼
