Very low-thrust trajectory optimization using a direct SQP method
This paper describes the application of the transcription method to the solution of very low-thrust orbit transfers. The vehicle dynamics are defined using a modified set of equinoctial coordinates, and the trajectory modeling is described using these dynamics. The aim is to determine the optimal thrust magnitude and direction, which minimizes the fuel consumed during the transfer between park orbit and mission orbit.
scientific article; zbMATH DE number 1501735