Abstract
The regularization of spacecraft motion equations by the Kustaanheimo-Stiefel transformation for coordinates and Sundman’s transformation for time in the case of interplanetary low-thrust optimal transfer is considered. From Pontryagin’s maximum principle, the thrust vector optimal control is derived under the limited power condition. The Earth-Mars transfer problem is solved in the regular variables. The comparison of calculated trajectories with the ones obtained by the parameter continuation method is performed, and the stability properties of the two-point boundary value problem in the Cartesian and regular variables are studied.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
