Homotopic approach of low-thrust trajectory optimization

Abstract

This paper addresses the homotopic approach's applications for optimizing and designing low thrust spacecraft trajectories using both indirect and direct methods. The indirect method's homotopic optimization approach was performed in orbital transfer and rendezvous problems in the two-body problem, and the direct method's homotopic optimization approach was performed with lunar capture trajectory in Circular Restricted Three-Body Problem (CRTBP). Algorithms for both methods are presented with various successfully converged solutions. It was found that the proposed methods of optimization were able to design and optimize the trajectory with given spacecraft parameters from the user.